def initial_sizing(nexus):
for config in nexus.vehicle_configurations:
config.mass_properties.max_zero_fuel = nexus.MZFW_ratio*config.mass_properties.max_takeoff
for wing in config.wings:
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
#compute atmosphere conditions for turbofan sizing
air_speed = nexus.missions.base.segments['cruise'].air_speed
altitude = nexus.missions.base.segments['climb_5'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude) #freestream conditions
mach_number = air_speed/freestream.speed_of_sound
freestream.mach_number = mach_number
freestream.velocity = air_speed
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
conditions.freestream = freestream
turbofan_sizing(config.propulsors['turbofan'], mach_number, altitude)
compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
# diff the new data
config.store_diff()
return nexus
def initial_sizing(nexus):
for config in nexus.vehicle_configurations:
config.mass_properties.max_zero_fuel = nexus.MZFW_ratio * config.mass_properties.max_takeoff
for wing in config.wings:
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(
wing)
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
#compute atmosphere conditions for turbofan sizing
air_speed = nexus.missions.base.segments['cruise'].air_speed
altitude = nexus.missions.base.segments['climb_5'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(
altitude) #freestream conditions
mach_number = air_speed / freestream.speed_of_sound
freestream.mach_number = mach_number
freestream.velocity = air_speed
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
conditions.freestream = freestream
turbofan_sizing(config.propulsors['turbofan'], mach_number, altitude)
compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
# diff the new data
config.store_diff()
return nexus
def simple_sizing(nexus):
configs = nexus.vehicle_configurations
base = configs.base
#find conditions
air_speed = nexus.missions.base.segments['cruise'].air_speed
altitude = nexus.missions.base.segments['climb_5'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude)
freestream0 = atmosphere.compute_values(6000. * Units.ft) #cabin altitude
diff_pressure = np.max(freestream0.pressure - freestream.pressure, 0)
fuselage = base.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
#now size engine
mach_number = air_speed / freestream.speed_of_sound
#now add to freestream data object
freestream.velocity = air_speed
freestream.mach_number = mach_number
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
) #assign conditions in form for propulsor sizing
conditions.freestream = freestream
for config in configs:
config.wings.horizontal_stabilizer.areas.reference = (
26.0 / 92.0) * config.wings.main_wing.areas.reference
for wing in config.wings:
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(
wing)
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
fuselage = config.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
turbofan_sizing(config.networks['turbofan'],
mach_number=mach_number,
altitude=altitude)
compute_turbofan_geometry(config.networks['turbofan'],
config.nacelles.nacelle_1)
return nexus
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'EMBRAER E190AR'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 51800.0 # kg
vehicle.mass_properties.operating_empty = 29100.0 # kg
vehicle.mass_properties.takeoff = 51800.0 # kg
## vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 0. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [60 * Units.feet, 0,
0] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [[10**5, 0, 0],
[
0,
10**6,
0,
], [0, 0, 10**7]
] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.0
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.4
wing.sweeps.quarter_chord = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.span_efficiency = 1.0
## wing.spans.projected = 27.8
##
## wing.chords.root = 5.203
## wing.chords.tip = 1.460
## wing.chords.mean_aerodynamic = 3.680
wing.areas.reference = 92.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.2, 0, 0] # Need to fix
## wing.aerodynamic_center = [3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = "double_slotted"
wing.flaps.chord = 0.280
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
## wing.spans.projected = 11.958
##
## wing.chords.root = 3.030
## wing.chords.tip = 0.883
## wing.chords.mean_aerodynamic = 2.3840
wing.areas.reference = 26.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [31., 0, 0] # need to fix
## wing.aerodynamic_center = [2,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.7 #
wing.sweeps.quarter_chord = 35 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.span_efficiency = 0.9
## wing.spans.projected = 5.270 #
##
## wing.chords.root = 4.70
## wing.chords.tip = 1.45
## wing.chords.mean_aerodynamic = 3.36
wing.areas.reference = 16.0 #
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [29.5, 0, 0]
## wing.aerodynamic_center = [2,0,0]
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
gt_engine.position[1] = 4.50
#compute engine areas
Awet = 1.1 * np.pi * gt_engine.nacelle_diameter * gt_engine.engine_length
#assign engine areas
gt_engine.areas.wetted = Awet
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 37278.0 * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
#create conditions object for sizing the turbofan
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
conditions = atmosphere.compute_values(altitude)
turbofan_sizing(gt_engine, mach_number, altitude)
compute_turbofan_geometry(gt_engine, conditions)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def energy_network():
# ------------------------------------------------------------------
# Evaluation Conditions
# ------------------------------------------------------------------
# --- Conditions
ones_1col = np.ones([1, 1])
# setup conditions
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
'''
conditions.frames = Data()
conditions.freestream = Data()
conditions.aerodynamics = Data()
conditions.propulsion = Data()
conditions.weights = Data()
conditions.energies = Data()
'''
# self.conditions = conditions
# freestream conditions
conditions.freestream.mach_number = ones_1col * 0.8
conditions.freestream.pressure = ones_1col * 20000.
conditions.freestream.temperature = ones_1col * 215.
conditions.freestream.density = ones_1col * 0.8
conditions.freestream.dynamic_viscosity = ones_1col * 0.000001475
conditions.freestream.altitude = ones_1col * 10.
conditions.freestream.gravity = ones_1col * 9.81
conditions.freestream.isentropic_expansion_factor = ones_1col * 1.4
conditions.freestream.Cp = 1.4 * 287.87 / (1.4 - 1)
conditions.freestream.R = 287.87
conditions.M = conditions.freestream.mach_number
conditions.T = conditions.freestream.temperature
conditions.p = conditions.freestream.pressure
conditions.freestream.speed_of_sound = ones_1col * np.sqrt(
conditions.freestream.Cp /
(conditions.freestream.Cp - conditions.freestream.R) *
conditions.freestream.R * conditions.freestream.temperature) #300.
conditions.freestream.velocity = conditions.M * conditions.freestream.speed_of_sound
conditions.velocity = conditions.M * conditions.freestream.speed_of_sound
conditions.q = 0.5 * conditions.freestream.density * conditions.velocity**2
conditions.g0 = conditions.freestream.gravity
# propulsion conditions
conditions.propulsion.throttle = ones_1col * 1.0
# ------------------------------------------------------------------
# Design/sizing conditions
# ------------------------------------------------------------------
# Conditions
ones_1col = np.ones([1, 1])
# Setup conditions
conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
)
'''
conditions_sizing.frames = Data()
conditions_sizing.freestream = Data()
conditions_sizing.aerodynamics = Data()
conditions_sizing.propulsion = Data()
conditions_sizing.weights = Data()
conditions_sizing.energies = Data()
'''
# self.conditions = conditions
# freestream conditions
conditions_sizing.freestream.mach_number = ones_1col * 0.8
conditions_sizing.freestream.pressure = ones_1col * 26499.73156529
conditions_sizing.freestream.temperature = ones_1col * 223.25186491
conditions_sizing.freestream.density = ones_1col * 0.41350854
conditions_sizing.freestream.dynamic_viscosity = ones_1col * 1.45766126e-05
conditions_sizing.freestream.altitude = ones_1col * 10000.
conditions_sizing.freestream.gravity = ones_1col * 9.81
conditions_sizing.freestream.isentropic_expansion_factor = ones_1col * 1.4
conditions_sizing.freestream.Cp = 1.4 * 287.87 / (1.4 - 1)
conditions_sizing.freestream.R = 287.87
conditions_sizing.freestream.speed_of_sound = 299.53150968
conditions_sizing.freestream.velocity = conditions_sizing.freestream.mach_number * conditions_sizing.freestream.speed_of_sound
# propulsion conditions
conditions_sizing.propulsion.throttle = ones_1col * 1.0
state_sizing = Data()
state_sizing.numerics = Data()
state_sizing.conditions = conditions_sizing
state_off_design = Data()
state_off_design.numerics = Data()
state_off_design.conditions = conditions
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# Instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.bypass_ratio = 5.4
turbofan.number_of_engines = 2.0
turbofan.engine_length = 2.5
turbofan.nacelle_diameter = 1.580
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# to compute thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'thrust'
# setup
thrust.total_design = 42383.01818423
# add to network
turbofan.thrust = thrust
numerics = Data()
eta = 1.0
#size the turbofan
turbofan_sizing(turbofan, 0.8, 10000.0)
print "Design thrust ", turbofan.design_thrust
print "Sealevel static thrust ", turbofan.sealevel_static_thrust
results_design = turbofan(state_sizing)
results_off_design = turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42383.01818402065
expected.mdot = 0.76425264
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust) / expected.thrust
error.mdot_error = (mdot[0][0] - expected.mdot) / expected.mdot
print error
for k, v in error.items():
assert (np.abs(v) < 1e-6)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.operating_empty = 62746.4 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 62732.0 # kg #0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [[
15.30987849, 0., -0.48023939
]]
vehicle.mass_properties.moments_of_inertia.tensor = [[
3173074.17, 0, 28752.77565
], [0, 3019041.443, 0], [0, 0, 5730017.433]] # estimated, not correct
vehicle.design_mach_number = 0.78
vehicle.design_range = 3582 * Units.miles
vehicle.design_cruise_alt = 35000.0 * Units.ft
# envelope properties
vehicle.envelope.ultimate_load = 3.75
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.1
wing.spans.projected = 34.32
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[13.61, 0, -1.27]]
wing.aerodynamic_center = [0, 0, 0] #[3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# Wing Segments
root_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
root_airfoil.coordinate_file = '../Vehicles/B737a.txt'
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Root'
segment.percent_span_location = 0.0
segment.twist = 4. * Units.deg
segment.root_chord_percent = 1.
segment.thickness_to_chord = 0.1
segment.dihedral_outboard = 2.5 * Units.degrees
segment.sweeps.quarter_chord = 28.225 * Units.degrees
segment.thickness_to_chord = .1
segment.append_airfoil(root_airfoil)
wing.append_segment(segment)
yehudi_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
yehudi_airfoil.coordinate_file = '../Vehicles/B737b.txt'
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Yehudi'
segment.percent_span_location = 0.324
segment.twist = (wing.twists.root *
(1 - segment.percent_span_location)) * Units.deg
segment.root_chord_percent = 0.5
segment.thickness_to_chord = 0.1
segment.dihedral_outboard = 5.5 * Units.degrees
segment.sweeps.quarter_chord = 25. * Units.degrees
segment.thickness_to_chord = .1
segment.append_airfoil(yehudi_airfoil)
wing.append_segment(segment)
mid_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
mid_airfoil.coordinate_file = '../Vehicles/B737c.txt'
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_2'
segment.percent_span_location = 0.963
segment.twist = (wing.twists.root *
(1 - segment.percent_span_location)) * Units.deg
segment.root_chord_percent = 0.220
segment.thickness_to_chord = 0.1
segment.dihedral_outboard = 5.5 * Units.degrees
segment.sweeps.quarter_chord = 56.75 * Units.degrees
segment.thickness_to_chord = .1
segment.append_airfoil(mid_airfoil)
wing.append_segment(segment)
tip_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
tip_airfoil.coordinate_file = '../Vehicles/B737d.txt'
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.degrees
segment.root_chord_percent = 0.10077
segment.thickness_to_chord = 0.1
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = .1
segment.append_airfoil(tip_airfoil)
wing.append_segment(segment)
# control surfaces -------------------------------------------
slat = SUAVE.Components.Wings.Control_Surfaces.Slat()
slat.tag = 'slat'
slat.span_fraction_start = 0.2
slat.span_fraction_end = 0.963
slat.deflection = 0.0 * Units.degrees
slat.chord_fraction = 0.075
wing.append_control_surface(slat)
flap = SUAVE.Components.Wings.Control_Surfaces.Flap()
flap.tag = 'flap'
flap.span_fraction_start = 0.2
flap.span_fraction_end = 0.7
flap.deflection = 0.0 * Units.degrees
flap.configuration_type = 'double_slotted'
flap.chord_fraction = 0.30
wing.append_control_surface(flap)
aileron = SUAVE.Components.Wings.Control_Surfaces.Aileron()
aileron.tag = 'aileron'
aileron.span_fraction_start = 0.7
aileron.span_fraction_end = 0.963
aileron.deflection = 0.0 * Units.degrees
aileron.chord_fraction = 0.16
wing.append_control_surface(aileron)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16 #
wing.sweeps.quarter_chord = 40 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.spans.projected = 14.2
wing.chords.root = 4.7
wing.chords.tip = .955
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.areas.exposed = 59.354 # Exposed area of the horizontal tail
wing.areas.wetted = 64.976 # Wetted area of the horizontal tail
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [[32.83, 0, 1.14]]
wing.aerodynamic_center = [0, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# Wing Segments
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'root_segment'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.0
segment.dihedral_outboard = 8.63 * Units.degrees
segment.sweeps.quarter_chord = 38.42 * Units.degrees
segment.thickness_to_chord = .1
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip_segment'
segment.percent_span_location = 1.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.203
segment.dihedral_outboard = 0 * Units.degrees
segment.sweeps.quarter_chord = 0 * Units.degrees
segment.thickness_to_chord = .1
wing.append_segment(segment)
# control surfaces -------------------------------------------
elevator = SUAVE.Components.Wings.Control_Surfaces.Elevator()
elevator.tag = 'elevator'
elevator.span_fraction_start = 0.09
elevator.span_fraction_end = 0.92
elevator.deflection = 0.0 * Units.deg
elevator.chord_fraction = 0.3
wing.append_control_surface(elevator)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91 #
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.spans.projected = 7.777
wing.total_length = wing.spans.projected
#
wing.chords.root = 8.19
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 27.316 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[28.79, 0, 1.54]]
wing.aerodynamic_center = [0, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# Wing Segments
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'root'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.
segment.dihedral_outboard = 0 * Units.degrees
segment.sweeps.quarter_chord = 63.63 * Units.degrees
segment.thickness_to_chord = .1
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'segment_1'
segment.percent_span_location = 0.194
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.540
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 30.0 * Units.degrees
segment.thickness_to_chord = .1
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'segment_2'
segment.percent_span_location = 1.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.175
segment.dihedral_outboard = 0.0 * Units.degrees
segment.sweeps.quarter_chord = 51.0 * Units.degrees
segment.thickness_to_chord = .1
wing.append_segment(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 31. * Units.inches
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85 #44.0
fuselage.lengths.total = 38.02 #58.4
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74 #4.
fuselage.heights.maximum = 3.74 #4. #
fuselage.heights.at_quarter_length = 3.74 # Not correct
fuselage.heights.at_three_quarters_length = 3.65 # Not correct
fuselage.heights.at_wing_root_quarter_chord = 3.74 # Not correct
fuselage.areas.side_projected = 142.1948 #4.* 59.8 # Not correct
fuselage.areas.wetted = 446.718 #688.64
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74 #4.0
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# This origin is overwritten by compute_component_centers_of_gravity(base,compute_propulsor_origin=True)
turbofan.origin = [[13.72, 4.86, -1.9], [13.72, -4.86, -1.9]]
#compute engine areas
Awet = 1.1 * np.pi * turbofan.nacelle_diameter * turbofan.engine_length
#Assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2 * 24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
turbofan.core_nozzle_diameter = 0.92
turbofan.fan_nozzle_diameter = 1.659
turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
turbofan.plug_diameter = 0.1 #dimater of the engine plug
turbofan.geometry_xe = 1. # Geometry information for the installation effects function
turbofan.geometry_ye = 1. # Geometry information for the installation effects function
turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
#size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Fuel
# ------------------------------------------------------------------
fuel = SUAVE.Components.Physical_Component()
vehicle.fuel = fuel
fuel.mass_properties.mass = vehicle.mass_properties.max_takeoff - vehicle.mass_properties.max_fuel
fuel.origin = vehicle.wings.main_wing.mass_properties.center_of_gravity
fuel.mass_properties.center_of_gravity = vehicle.wings.main_wing.aerodynamic_center
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 1 #number of nose landing gear
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.operating_empty = 62746.4 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 62732.0 # kg #0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [ 15.30987849, 0. , -0.48023939]
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
#used for noise calculations
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear=landing_gear
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.1
wing.span_efficiency = 0.9
wing.spans.projected = 34.32
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.61,0,-1.27]
wing.aerodynamic_center = [0,0,0] #[3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30
wing.flaps.span_start = 0.10 # -> wing.flaps.area = 97.1112
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_slotted' # -> wing.flaps.number_slots = 2
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16 #
wing.sweeps.quarter_chord = 40 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.span_efficiency = 0.9
wing.spans.projected = 14.2
wing.chords.root = 4.7
wing.chords.tip = .955
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.areas.exposed = 59.354 # Exposed area of the horizontal tail
wing.areas.wetted = 64.976 # Wetted area of the horizontal tail
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [32.83,0,1.14]
wing.aerodynamic_center = [0,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91 #
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.777 #
wing.chords.root = 8.19
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 27.316 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [28.79,0,1.54]
wing.aerodynamic_center = [0,0,0] #[2,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
#fuselage.number_coach_seats = 200.
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85 #44.0
fuselage.lengths.total = 38.02 #58.4
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74 #4.
fuselage.heights.maximum = 3.74 #4. #
fuselage.heights.at_quarter_length = 3.74 # Not correct
fuselage.heights.at_three_quarters_length = 3.65 # Not correct
fuselage.heights.at_wing_root_quarter_chord = 3.74 # Not correct
fuselage.areas.side_projected = 142.1948 #4.* 59.8 # Not correct
fuselage.areas.wetted = 446.718 #688.64
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74 #4.0
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# This origin is overwritten by compute_component_centers_of_gravity(base,compute_propulsor_origin=True)
turbofan.origin = [[13.72, 4.86,-1.9],[13.72, -4.86,-1.9]]
#compute engine areas
Awet = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
#Assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
turbofan.core_nozzle_diameter = 0.92
turbofan.fan_nozzle_diameter = 1.659
turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
turbofan.plug_diameter = 0.1 #dimater of the engine plug
turbofan.geometry_xe = 1. # Geometry information for the installation effects function
turbofan.geometry_ye = 1. # Geometry information for the installation effects function
turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.operating_empty = 62746.4 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [60 * Units.feet, 0, 0]
vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]]
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.16
wing.span_efficiency = 0.9
wing.spans.projected = 35.66
wing.chords.root = 6.81
wing.chords.tip = 1.09
wing.chords.mean_aerodynamic = 4.235
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = -4.0 * Units.degrees
wing.origin = [20,0,0]
wing.aerodynamic_center = [3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweep = 30 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.4
wing.span_efficiency = 0.9
wing.spans.projected = 14.146
wing.chords.root = 3.28
wing.chords.tip = 1.31
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [50,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.877
wing.chords.root = 6.60
wing.chords.tip = 1.65
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85
fuselage.lengths.total = 38.02
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74
fuselage.heights.maximum = 3.74
fuselage.heights.at_quarter_length = 3.74
fuselage.heights.at_three_quarters_length = 3.74
fuselage.heights.at_wing_root_quarter_chord = 3.74
fuselage.areas.side_projected = 142.1948
fuselage.areas.wetted = 446.718
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74 #4.0
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbo_fan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_BWB_450'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 823000. * Units.lb
vehicle.mass_properties.takeoff = 823000. * Units.lb
vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 00. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 7840. * 2 * Units.feet**2
vehicle.passengers = 450.
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 289.**2 / (7840. * 2)
wing.thickness_to_chord = 0.15
wing.taper = 0.0138
wing.spans.projected = 289.0 * Units.feet
wing.chords.root = 145.0 * Units.feet
wing.chords.tip = 3.5 * Units.feet
wing.chords.mean_aerodynamic = 80. * Units.feet
wing.areas.reference = 7840. * 2 * Units.feet**2
wing.sweeps.quarter_chord = 33. * Units.degrees
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dihedral = 2.5 * Units.degrees
wing.origin = [[0.,0.,0]]
wing.aerodynamic_center = [0,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 40.0 * Units.degrees
segment.thickness_to_chord = 0.165
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 4.
segment.vsp_mesh.outer_radius = 4.
segment.vsp_mesh.inner_length = .14
segment.vsp_mesh.outer_length = .14
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 0.052
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.921
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 52.5 * Units.degrees
segment.thickness_to_chord = 0.167
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 4.
segment.vsp_mesh.outer_radius = 4.
segment.vsp_mesh.inner_length = .14
segment.vsp_mesh.outer_length = .14
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_3'
segment.percent_span_location = 0.138
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.76
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 36.9 * Units.degrees
segment.thickness_to_chord = 0.171
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 4.
segment.vsp_mesh.outer_radius = 4.
segment.vsp_mesh.inner_length = .14
segment.vsp_mesh.outer_length = .14
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_4'
segment.percent_span_location = 0.221
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.624
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 30.4 * Units.degrees
segment.thickness_to_chord = 0.175
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 4.
segment.vsp_mesh.outer_radius = 2.8
segment.vsp_mesh.inner_length = .14
segment.vsp_mesh.outer_length = .14
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_5'
segment.percent_span_location = 0.457
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.313
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 30.85 * Units.degrees
segment.thickness_to_chord = 0.118
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_6'
segment.percent_span_location = 0.568
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.197
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 34.3 * Units.degrees
segment.thickness_to_chord = 0.10
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_7'
segment.percent_span_location = 0.97
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.086
segment.dihedral_outboard = 73. * Units.degrees
segment.sweeps.quarter_chord = 55. * Units.degrees
segment.thickness_to_chord = 0.10
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.0241
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 0. * Units.degrees
segment.thickness_to_chord = 0.10
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan1'
# setup
turbofan.number_of_engines = 3.0
turbofan.bypass_ratio = 8.1
turbofan.engine_length = 289. * Units.inches
turbofan.nacelle_diameter = 3.96 * Units.meters
#turbofan.cooling_ratio = 1.0
turbofan.origin = [[133.0 *Units.feet, 25.0*Units.feet, 6.5*Units.feet],[145.0 *Units.feet, 0.0*Units.feet, 6.5*Units.feet],[133.0 *Units.feet, -25.0*Units.feet, 6.5*Units.feet]]
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 1.0
inlet_nozzle.pressure_ratio = 1.0
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.1
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 23.0
#compressor.hub_to_tip_ratio = 0.325
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 1.0
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1592. * Units.kelvin
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.58
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2.0*512000 * Units.N
thrust.bypass_ratio = 8.4
#design sizing conditions
altitude = 0. * Units.km
mach_number = 0.01
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
#turbofan.size(mach_number,altitude)
#computing the engine length and diameter
compute_turbofan_geometry(turbofan,None)
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = "Embraer_E190"
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 51800.0 # kg
vehicle.mass_properties.operating_empty = 27837.0 # kg
vehicle.mass_properties.takeoff = 50989.0 # 51800. # kg
vehicle.mass_properties.max_zero_fuel = 40900.0 # kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 13063.0 * Units.kg
vehicle.mass_properties.max_fuel = 12971.0
vehicle.mass_properties.center_of_gravity = [60 * Units.feet, 0, 0] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [
[10 ** 5, 0, 0],
[0, 10 ** 6, 0],
[0, 0, 10 ** 7],
] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.00
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = "main_wing"
wing.aspect_ratio = 8.4
wing.sweep = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.span_efficiency = 1.0
wing.spans.projected = 27.8
wing.chords.root = 5.203
wing.chords.tip = 1.460
wing.chords.mean_aerodynamic = 3.680
wing.areas.reference = 92.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [20, 0, 0]
wing.aerodynamic_center = [3, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = "horizontal_stabilizer"
wing.aspect_ratio = 5.5
wing.sweep = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
wing.spans.projected = 11.958
wing.chords.root = 3.030
wing.chords.tip = 0.883
wing.chords.mean_aerodynamic = 2.3840
wing.areas.reference = 26.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [35, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = "vertical_stabilizer"
wing.aspect_ratio = 1.7 #
wing.sweep = 35 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.span_efficiency = 0.9
wing.spans.projected = 5.270 #
wing.chords.root = 4.70
wing.chords.tip = 1.45
wing.chords.mean_aerodynamic = 3.36
wing.areas.reference = 16.0 #
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [35, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = "fuselage"
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0
fuselage.lengths.tail = 9.0
fuselage.lengths.cabin = 21.24
fuselage.lengths.total = 36.24
fuselage.lengths.fore_space = 0.0
fuselage.lengths.aft_space = 0.0
fuselage.width = 3.18
fuselage.heights.maximum = 4.18 #
fuselage.heights.at_quarter_length = 3.18 # Not correct
fuselage.heights.at_three_quarters_length = 3.18 # Not correct
fuselage.heights.at_wing_root_quarter_chord = 4.00 # Not correct
fuselage.areas.side_projected = 239.20
fuselage.areas.wetted = 327.01
fuselage.areas.front_projected = 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10 ** 5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = "turbo_fan"
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
# set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
# add working fluid to the network
gt_engine.working_fluid = working_fluid
# Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = "ram"
# add ram to the network
gt_engine.ram = ram
# Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = "inlet nozzle"
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = "lpc"
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = "hpc"
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag = "lpt"
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag = "hpt"
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = "Comb"
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = "core nozzle"
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
# add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = "fan nozzle"
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = "fan"
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add the fan to the network
gt_engine.fan = fan
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = "compute_thrust"
# total design thrust (includes all the engines)
thrust.total_design = 37278.0 * Units.N # Newtons
# design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.0
# add thrust to the network
gt_engine.thrust = thrust
# size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_BWB_450'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 823000. * Units.lb
vehicle.mass_properties.takeoff = 823000. * Units.lb
vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 0. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 15680. * Units.feet**2
vehicle.passengers = 450.
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 289.**2 / (7840. * 2)
wing.thickness_to_chord = 0.15
wing.taper = 0.0138
wing.span_efficiency = 0.95
wing.spans.projected = 289.0 * Units.feet
wing.chords.root = 145.0 * Units.feet
wing.chords.tip = 3.5 * Units.feet
wing.chords.mean_aerodynamic = 86. * Units.feet
wing.areas.reference = 15680. * Units.feet**2
wing.sweeps.quarter_chord = 33. * Units.degrees
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dihedral = 2.5 * Units.degrees
wing.origin = [0.,0.,0]
wing.aerodynamic_center = [0,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 30.0 * Units.degrees
segment.thickness_to_chord = 0.165
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 0.052
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.921
segment.dihedral_outboard = 0. * Units.degrees
segment.sweeps.quarter_chord = 52.5 * Units.degrees
segment.thickness_to_chord = 0.167
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_3'
segment.percent_span_location = 0.138
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.76
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 36.9 * Units.degrees
segment.thickness_to_chord = 0.171
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_4'
segment.percent_span_location = 0.221
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.624
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 30.4 * Units.degrees
segment.thickness_to_chord = 0.175
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_5'
segment.percent_span_location = 0.457
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.313
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 30.85 * Units.degrees
segment.thickness_to_chord = 0.118
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_6'
segment.percent_span_location = 0.568
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.197
segment.dihedral_outboard = 1.85 * Units.degrees
segment.sweeps.quarter_chord = 34.3 * Units.degrees
segment.thickness_to_chord = 0.10
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_7'
segment.percent_span_location = 0.97
segment.twist = 0. * Units.deg
segment.root_chord_percent = 0.086
segment.dihedral_outboard = 73. * Units.degrees
segment.sweeps.quarter_chord = 55. * Units.degrees
segment.thickness_to_chord = 0.10
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan1'
# setup
turbofan.number_of_engines = 3.0
turbofan.bypass_ratio = 8.1
turbofan.engine_length = 289. * Units.inches
turbofan.nacelle_diameter = 3.96 * Units.meters
turbofan.origin = [[133.0 *Units.feet, 25.0*Units.feet, 6.5*Units.feet],[145.0 *Units.feet, 0.0*Units.feet, 6.5*Units.feet],[133.0 *Units.feet, -25.0*Units.feet, 6.5*Units.feet]]
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 1.0
inlet_nozzle.pressure_ratio = 1.0
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.1
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 23.0
#compressor.hub_to_tip_ratio = 0.325
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 1.0
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1592. * Units.kelvin
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.58
#fan.hub_to_tip_ratio = 0.325
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 3.0*512000 * Units.N
thrust.bypass_ratio = 8.4
#design sizing conditions
altitude = 0. * Units.km
mach_number = 0.01
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
#computing the engine length and diameter
compute_turbofan_geometry(turbofan,None)
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def energy_network():
# ------------------------------------------------------------------
# Evaluation Conditions
# ------------------------------------------------------------------
# --- Conditions
ones_1col = np.ones([1,1])
# setup conditions
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
'''
conditions.frames = Data()
conditions.freestream = Data()
conditions.aerodynamics = Data()
conditions.propulsion = Data()
conditions.weights = Data()
conditions.energies = Data()
'''
# self.conditions = conditions
# freestream conditions
conditions.freestream.mach_number = ones_1col*0.8
conditions.freestream.pressure = ones_1col*20000.
conditions.freestream.temperature = ones_1col*215.
conditions.freestream.density = ones_1col*0.8
conditions.freestream.dynamic_viscosity = ones_1col* 0.000001475
conditions.freestream.altitude = ones_1col* 10.
conditions.freestream.gravity = ones_1col*9.81
conditions.freestream.gamma = ones_1col*1.4
conditions.freestream.Cp = 1.4*287.87/(1.4-1)
conditions.freestream.R = 287.87
conditions.M = conditions.freestream.mach_number
conditions.T = conditions.freestream.temperature
conditions.p = conditions.freestream.pressure
conditions.freestream.speed_of_sound = ones_1col* np.sqrt(conditions.freestream.Cp/(conditions.freestream.Cp-conditions.freestream.R)*conditions.freestream.R*conditions.freestream.temperature) #300.
conditions.freestream.velocity = conditions.M * conditions.freestream.speed_of_sound
conditions.velocity = conditions.M * conditions.freestream.speed_of_sound
conditions.q = 0.5*conditions.freestream.density*conditions.velocity**2
conditions.g0 = conditions.freestream.gravity
# propulsion conditions
conditions.propulsion.throttle = ones_1col*1.0
# ------------------------------------------------------------------
# Design/sizing conditions
# ------------------------------------------------------------------
# --- Conditions
ones_1col = np.ones([1,1])
# setup conditions
conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
'''
conditions_sizing.frames = Data()
conditions_sizing.freestream = Data()
conditions_sizing.aerodynamics = Data()
conditions_sizing.propulsion = Data()
conditions_sizing.weights = Data()
conditions_sizing.energies = Data()
'''
# self.conditions = conditions
# freestream conditions
conditions_sizing.freestream.mach_number = ones_1col*0.8
conditions_sizing.freestream.pressure = ones_1col*26499.73156529
conditions_sizing.freestream.temperature = ones_1col*223.25186491
conditions_sizing.freestream.density = ones_1col*0.41350854
conditions_sizing.freestream.dynamic_viscosity = ones_1col* 1.45766126e-05 #*1.789*10**(-5)
conditions_sizing.freestream.altitude = ones_1col* 10000. #* 0.5
conditions_sizing.freestream.gravity = ones_1col*9.81
conditions_sizing.freestream.gamma = ones_1col*1.4
conditions_sizing.freestream.Cp = 1.4*287.87/(1.4-1)
conditions_sizing.freestream.R = 287.87
conditions_sizing.freestream.speed_of_sound = 299.53150968
conditions_sizing.freestream.velocity = conditions_sizing.freestream.mach_number * conditions_sizing.freestream.speed_of_sound
# propulsion conditions
conditions_sizing.propulsion.throttle = ones_1col*1.0
state_sizing = Data()
state_sizing.numerics = Data()
state_sizing.conditions = conditions_sizing
state_off_design=Data()
state_off_design.numerics=Data()
state_off_design.conditions=conditions
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbo_fan'
# setup
turbofan.bypass_ratio = 5.4
turbofan.number_of_engines = 2.0
turbofan.engine_length = 2.5
turbofan.nacelle_diameter = 1.580
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# to compute thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design =42383.01818423
# add to network
turbofan.thrust = thrust
#bypass ratio closer to fan
numerics = Data()
eta=1.0
#size the turbofan
turbofan_sizing(turbofan,0.8,10000.0)
print "Design thrust ",turbofan.design_thrust
print "Sealevel static thrust ",turbofan.sealevel_static_thrust
results_design = turbofan(state_sizing)
results_off_design=turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design=results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42383.01818423
expected.mdot = 0.7657905
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0]-expected.mdot)/expected.mdot
print error
for k,v in error.items():
assert(np.abs(v)<1e-4)
return
def vehicle_setup():
"""This is the full physical definition of the vehicle, and is designed to be independent of the
analyses that are selected."""
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737-800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# Vehicle level mass properties
# The maximum takeoff gross weight is used by a number of methods, most notably the weight
# method. However, it does not directly inform mission analysis.
vehicle.mass_properties.max_takeoff = 79015.8 * Units.kilogram
# The takeoff weight is used to determine the weight of the vehicle at the start of the mission
vehicle.mass_properties.takeoff = 79015.8 * Units.kilogram
# Operating empty may be used by various weight methods or other methods. Importantly, it does
# not constrain the mission analysis directly, meaning that the vehicle weight in a mission
# can drop below this value if more fuel is needed than is available.
vehicle.mass_properties.operating_empty = 62746.4 * Units.kilogram
# The maximum zero fuel weight is also used by methods such as weights
vehicle.mass_properties.max_zero_fuel = 62732.0 * Units.kilogram
# Cargo weight typically feeds directly into weights output and does not affect the mission
vehicle.mass_properties.cargo = 10000. * Units.kilogram
# Envelope properties
# These values are typical FAR values for a transport of this type
vehicle.envelope.ultimate_load = 3.75
vehicle.envelope.limit_load = 2.5
# Vehicle level parameters
# The vehicle reference area typically matches the main wing reference area
vehicle.reference_area = 124.862 * Units['meters**2']
# Number of passengers, control settings, and accessories settings are used by the weights
# methods
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
# The settings here can be used for noise analysis, but are not used in this tutorial
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 # Number of main landing gear
landing_gear.nose_units = 1 # Number of nose landing gear
landing_gear.main_wheels = 2 # Number of wheels on the main landing gear
landing_gear.nose_wheels = 2 # Number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
# This main wing is approximated as a simple trapezoid. A segmented wing can also be created if
# desired. Segmented wings appear in later tutorials, and a version of the 737 with segmented
# wings can be found in the SUAVE testing scripts.
# SUAVE allows conflicting geometric values to be set in terms of items such as aspect ratio
# when compared with span and reference area. Sizing scripts may be used to enforce
# consistency if desired.
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
# Quarter chord sweep is used as the driving sweep in most of the low fidelity analysis methods.
# If a different known value (such as leading edge sweep) is given, it should be converted to
# quarter chord sweep and added here. In some cases leading edge sweep will be used directly as
# well, and can be entered here too.
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.1
wing.spans.projected = 34.32 * Units.meter
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862 * Units['meters**2']
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[13.61, 0, -1.27]] * Units.meter
wing.vertical = False
wing.symmetric = True
# The high lift flag controls aspects of maximum lift coefficient calculations
wing.high_lift = True
# The dynamic pressure ratio is used in stability calculations
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Main Wing Control Surfaces
# ------------------------------------------------------------------
# Information in this section is used for high lift calculations and when conversion to AVL
# is desired.
# Deflections will typically be specified separately in individual vehicle configurations.
flap = SUAVE.Components.Wings.Control_Surfaces.Flap()
flap.tag = 'flap'
flap.span_fraction_start = 0.20
flap.span_fraction_end = 0.70
flap.deflection = 0.0 * Units.degrees
# Flap configuration types are used in computing maximum CL and noise
flap.configuration_type = 'double_slotted'
flap.chord_fraction = 0.30
wing.append_control_surface(flap)
slat = SUAVE.Components.Wings.Control_Surfaces.Slat()
slat.tag = 'slat'
slat.span_fraction_start = 0.324
slat.span_fraction_end = 0.963
slat.deflection = 0.0 * Units.degrees
slat.chord_fraction = 0.1
wing.append_control_surface(slat)
aileron = SUAVE.Components.Wings.Control_Surfaces.Aileron()
aileron.tag = 'aileron'
aileron.span_fraction_start = 0.7
aileron.span_fraction_end = 0.963
aileron.deflection = 0.0 * Units.degrees
aileron.chord_fraction = 0.16
wing.append_control_surface(aileron)
# Add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweeps.quarter_chord = 40.0 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.spans.projected = 14.2 * Units.meter
wing.chords.root = 4.7 * Units.meter
wing.chords.tip = 0.955 * Units.meter
wing.chords.mean_aerodynamic = 3.0 * Units.meter
wing.areas.reference = 32.488 * Units['meters**2']
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [[32.83 * Units.meter, 0, 1.14 * Units.meter]]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# Add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweeps.quarter_chord = 25. * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.spans.projected = 7.777 * Units.meter
wing.chords.root = 8.19 * Units.meter
wing.chords.tip = 0.95 * Units.meter
wing.chords.mean_aerodynamic = 4.0 * Units.meter
wing.areas.reference = 27.316 * Units['meters**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[28.79 * Units.meter, 0, 1.54 * Units.meter]] # meters
wing.vertical = True
wing.symmetric = False
# The t tail flag is used in weights calculations
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# Add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
# Number of coach seats is used in some weights methods
fuselage.number_coach_seats = vehicle.passengers
# The seats abreast can be used along with seat pitch and the number of coach seats to
# determine the length of the cabin if desired.
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1 * Units.meter
# Fineness ratios are used to determine VLM fuselage shape and sections to use in OpenVSP
# output
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
# Nose and tail lengths are used in the VLM setup
fuselage.lengths.nose = 6.4 * Units.meter
fuselage.lengths.tail = 8.0 * Units.meter
fuselage.lengths.total = 38.02 * Units.meter
# Fore and aft space are added to the cabin length if the fuselage is sized based on
# number of seats
fuselage.lengths.fore_space = 6. * Units.meter
fuselage.lengths.aft_space = 5. * Units.meter
fuselage.width = 3.74 * Units.meter
fuselage.heights.maximum = 3.74 * Units.meter
fuselage.effective_diameter = 3.74 * Units.meter
fuselage.areas.side_projected = 142.1948 * Units['meters**2']
fuselage.areas.wetted = 446.718 * Units['meters**2']
fuselage.areas.front_projected = 12.57 * Units['meters**2']
# Maximum differential pressure between the cabin and the atmosphere
fuselage.differential_pressure = 5.0e4 * Units.pascal
# Heights at different longitudinal locations are used in stability calculations and
# in output to OpenVSP
fuselage.heights.at_quarter_length = 3.74 * Units.meter
fuselage.heights.at_three_quarters_length = 3.65 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.74 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
# For some methods, the 'turbofan' tag is still necessary. This will be changed in the
# future to allow arbitrary tags.
turbofan.tag = 'turbofan'
# High-level setup
turbofan.number_of_engines = 2
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71 * Units.meter
turbofan.nacelle_diameter = 2.05 * Units.meter
turbofan.origin = [[13.72, 4.86, -1.9], [13.72, -4.86, -1.9]] * Units.meter
# Approximate the wetted area
turbofan.areas.wetted = 1.1 * np.pi * turbofan.nacelle_diameter * turbofan.engine_length
# Establish the correct working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# Components use estimated efficiencies. Estimates by technology level can be
# found in textbooks such as those by J.D. Mattingly
# ------------------------------------------------------------------
# Component 1 - Ram
# Converts freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# Create component
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# Specify performance
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# Add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# Create component
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# Specify performance
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# Add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# Create component
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# Specify performance
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# Add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# Create component
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# Specify performance
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# Add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# Create component
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# Specify performance
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# Add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# Create component
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# Specify performance
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450 # K
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# Add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# Create component
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# Specify performance
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# Add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# Create component
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# Specify performance
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# Add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# Create component
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# Specify performance
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# Add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 11 - thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
# Design thrust is used to determine mass flow at full throttle
thrust.total_design = 2 * 24000. * Units.N #Newtons
# Add to network
turbofan.thrust = thrust
# Design sizing conditions are also used to determine mass flow
altitude = 35000.0 * Units.ft
mach_number = 0.78
# Determine turbofan behavior at the design condition
turbofan_sizing(turbofan, mach_number, altitude)
# Add turbofan network to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def engine_caluclations(altitude, bypass, mach_number, num_engine, thrust_total):
# initialize the gas turbine network
gt_engine = Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = num_engine
gt_engine.bypass_ratio = bypass
# gt_engine.engine_length = 5.2
gt_engine.nacelle_diameter = 3.5
# set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
# add working fluid to the network
gt_engine.working_fluid = working_fluid
# Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add ram to the network
gt_engine.ram = ram
# Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.90
low_pressure_compressor.pressure_ratio = 1.5
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.90 # FIXME
high_pressure_compressor.pressure_ratio = 14
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# Component 5 :low pressure turbine
low_pressure_turbine = Turbine_saga.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.89
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# Component 5 :high pressure turbine
high_pressure_turbine = Turbine_saga.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.89
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.995
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.96
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
# add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.89
fan.pressure_ratio = 1.5
# add the fan to the network
gt_engine.fan = fan
# Component 10 : Payload power draw
generator = Generator()
generator.tag = 'generator'
generator.power_draw = 1 / gt_engine.number_of_engines
gt_engine.generator = generator
# Engine setup for noise module
gt_engine.core_nozzle_diameter = 0.92
gt_engine.fan_nozzle_diameter = 1.659
gt_engine.engine_height = 1.35 # Engine centerline heigh above the ground plane
gt_engine.exa = 1 # distance from fan face to fan exit/ fan diameter)
gt_engine.plug_diameter = 0.1 # dimater of the engine plug
gt_engine.geometry_xe = 1. # Geometry information for the installation effects function
gt_engine.geometry_ye = 1. # Geometry information for the installation effects function
gt_engine.geometry_Ce = 2. # Geometry information for the installation effects function
# Define OPR
OPR = fan.pressure_ratio * high_pressure_compressor.pressure_ratio * low_pressure_compressor.pressure_ratio
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
# total design thrust (includes all the engines)
thrust.total_design = thrust_total # should be just a pointer not a number
# add thrust to the network
gt_engine.thrust = thrust
gt_engine.OPR = OPR
# print thrust
# size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
compute_turbofan_geometry(gt_engine, None)
return gt_engine
def energy_network():
# ------------------------------------------------------------------
# Evaluation Conditions
# ------------------------------------------------------------------
# Conditions
ones_1col = np.ones([1, 1])
alt = 10.0
# Setup conditions
planet = SUAVE.Attributes.Planets.Earth()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmo_data = atmosphere.compute_values(alt, 0, True)
working_fluid = SUAVE.Attributes.Gases.Air()
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
# freestream conditions
conditions.freestream.altitude = ones_1col * alt
conditions.freestream.mach_number = ones_1col * 0.8
conditions.freestream.pressure = ones_1col * atmo_data.pressure
conditions.freestream.temperature = ones_1col * atmo_data.temperature
conditions.freestream.density = ones_1col * atmo_data.density
conditions.freestream.dynamic_viscosity = ones_1col * atmo_data.dynamic_viscosity
conditions.freestream.gravity = ones_1col * planet.compute_gravity(alt)
conditions.freestream.isentropic_expansion_factor = ones_1col * working_fluid.compute_gamma(
atmo_data.temperature, atmo_data.pressure)
conditions.freestream.Cp = ones_1col * working_fluid.compute_cp(
atmo_data.temperature, atmo_data.pressure)
conditions.freestream.R = ones_1col * working_fluid.gas_specific_constant
conditions.freestream.speed_of_sound = ones_1col * atmo_data.speed_of_sound
conditions.freestream.velocity = conditions.freestream.mach_number * conditions.freestream.speed_of_sound
conditions.velocity = conditions.freestream.mach_number * conditions.freestream.speed_of_sound
conditions.q = 0.5 * conditions.freestream.density * conditions.velocity**2
conditions.g0 = conditions.freestream.gravity
# propulsion conditions
conditions.propulsion.throttle = ones_1col * 1.0
# ------------------------------------------------------------------
# Design/sizing conditions
# ------------------------------------------------------------------
# Conditions
ones_1col = np.ones([1, 1])
alt_size = 10000.0
# Setup conditions
planet = SUAVE.Attributes.Planets.Earth()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmo_data = atmosphere.compute_values(alt_size, 0, True)
working_fluid = SUAVE.Attributes.Gases.Air()
conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
)
# freestream conditions
conditions_sizing.freestream.altitude = ones_1col * alt_size
conditions_sizing.freestream.mach_number = ones_1col * 0.8
conditions_sizing.freestream.pressure = ones_1col * atmo_data.pressure
conditions_sizing.freestream.temperature = ones_1col * atmo_data.temperature
conditions_sizing.freestream.density = ones_1col * atmo_data.density
conditions_sizing.freestream.dynamic_viscosity = ones_1col * atmo_data.dynamic_viscosity
conditions_sizing.freestream.gravity = ones_1col * planet.compute_gravity(
alt_size)
conditions_sizing.freestream.isentropic_expansion_factor = ones_1col * working_fluid.compute_gamma(
atmo_data.temperature, atmo_data.pressure)
conditions_sizing.freestream.Cp = ones_1col * working_fluid.compute_cp(
atmo_data.temperature, atmo_data.pressure)
conditions_sizing.freestream.R = ones_1col * working_fluid.gas_specific_constant
conditions_sizing.freestream.speed_of_sound = ones_1col * atmo_data.speed_of_sound
conditions_sizing.freestream.velocity = conditions_sizing.freestream.mach_number * conditions_sizing.freestream.speed_of_sound
conditions_sizing.velocity = conditions_sizing.freestream.mach_number * conditions_sizing.freestream.speed_of_sound
conditions_sizing.q = 0.5 * conditions_sizing.freestream.density * conditions_sizing.velocity**2
conditions_sizing.g0 = conditions_sizing.freestream.gravity
# propulsion conditions
conditions_sizing.propulsion.throttle = ones_1col * 1.0
state_sizing = Data()
state_sizing.numerics = Data()
state_sizing.conditions = conditions_sizing
state_off_design = Data()
state_off_design.numerics = Data()
state_off_design.conditions = conditions
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# Instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.bypass_ratio = 5.4
turbofan.number_of_engines = 2.0
turbofan.engine_length = 2.5
turbofan.nacelle_diameter = 1.580
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'thrust'
# setup
thrust.total_design = 42383.01818423
# add to network
turbofan.thrust = thrust
numerics = Data()
eta = 1.0
#size the turbofan
turbofan_sizing(turbofan, 0.8, 10000.0)
print("Design thrust ", turbofan.design_thrust)
print("Sealevel static thrust ", turbofan.sealevel_static_thrust)
results_design = turbofan(state_sizing)
results_off_design = turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42360.88505056
expected.mdot = 0.76399257
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust) / expected.thrust
error.mdot_error = (mdot[0][0] - expected.mdot) / expected.mdot
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737_800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18 # Not set
wing.thickness_to_chord = 0.1 # Not set
wing.taper = 0.1
wing.span_efficiency = 0.9
wing.spans.projected = 34.32
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862 # Not set
wing.sweeps.quarter_chord = 25. * Units.degrees
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dihedral = 2.5 * Units.degrees
wing.origin = [13.61, 0, -1.27]
wing.aerodynamic_center = [0, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16 # Not set
wing.thickness_to_chord = 0.08 # Not set
wing.taper = 0.2
wing.span_efficiency = 0.9
wing.spans.projected = 14.2
wing.chords.root = 4.70
wing.chords.tip = 0.955
wing.chords.mean_aerodynamic = 2.5
wing.areas.reference = 42.65
wing.twists.root = 0.0 * Units.degrees # Not set
wing.twists.tip = 0.0 * Units.degrees # Not set
wing.sweeps.quarter_chord = 40.0 * Units.degrees
wing.origin = [32.83, 0, 1.14]
wing.aerodynamic_center = [0, 0, 0]
wing.dihedral = 8.63 * Units.degrees
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweeps.quarter_chord = 25. * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.77
wing.chords.root = 8.19
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 27.316
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [28.79, 0, 1.54]
wing.aerodynamic_center = [0, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.57
fuselage.fineness.tail = 3.2
fuselage.lengths.nose = 8.0
fuselage.lengths.tail = 12.
fuselage.lengths.cabin = 28.85
fuselage.lengths.total = 38.02
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.76
fuselage.heights.maximum = 3.76
fuselage.heights.at_quarter_length = 3.76
fuselage.heights.at_three_quarters_length = 3.65
fuselage.heights.at_wing_root_quarter_chord = 3.76
fuselage.areas.side_projected = 142.1948
fuselage.areas.wetted = 446.718
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.76
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 4.1
turbofan.nacelle_diameter = 0.85
turbofan.origin = [[13.72, 4.86, -1.9], [13.72, -4.86, -1.9]]
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2 * 24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
#computing the engine length and diameter
compute_turbofan_geometry(turbofan, None)
print "sls thrust : ", turbofan.sealevel_static_thrust
print "engine length : ", turbofan.engine_length
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190AR'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties (http://www.embraercommercialaviation.com/AircraftPDF/E190_Weights.pdf)
vehicle.mass_properties.max_takeoff = 51800. # kg
vehicle.mass_properties.operating_empty = 27837. # kg
vehicle.mass_properties.takeoff = 51800. # kg
vehicle.mass_properties.max_zero_fuel = 40900. # kg
vehicle.mass_properties.max_payload = 13063. # kg
vehicle.mass_properties.max_fuel = 12971. # kg
vehicle.mass_properties.cargo = 0.0 # kg
vehicle.mass_properties.center_of_gravity = [[16.8, 0, 1.6]]
vehicle.mass_properties.moments_of_inertia.tensor = [[10**5, 0, 0],
[
0,
10**6,
0,
], [0, 0, 10**7]]
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.
vehicle.passengers = 106
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = 92.0
wing.aspect_ratio = 8.4
wing.chords.root = 6.2
wing.chords.tip = 1.44
wing.sweeps.quarter_chord = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.dihedral = 5.00 * Units.deg
wing.spans.projected = 28.72
wing.origin = [[13.0, 0, -1.50]]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.areas.exposed = 0.80 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dynamic_pressure_ratio = 1.0
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'root'
segment.percent_span_location = 0.0
segment.twist = 4. * Units.deg
segment.root_chord_percent = 1.
segment.thickness_to_chord = .11
segment.dihedral_outboard = 5. * Units.degrees
segment.sweeps.quarter_chord = 20.6 * Units.degrees
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'yehudi'
segment.percent_span_location = 0.348
segment.twist = (4. - segment.percent_span_location * 4.) * Units.deg
segment.root_chord_percent = 0.60
segment.thickness_to_chord = .11
segment.dihedral_outboard = 4 * Units.degrees
segment.sweeps.quarter_chord = 24.1 * Units.degrees
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 0.961
segment.twist = (4. - segment.percent_span_location * 4.) * Units.deg
segment.root_chord_percent = 0.25
segment.thickness_to_chord = .11
segment.dihedral_outboard = 70. * Units.degrees
segment.sweeps.quarter_chord = 50. * Units.degrees
wing.Segments.append(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Tip'
segment.percent_span_location = 1.
segment.twist = (4. - segment.percent_span_location * 4.) * Units.deg
segment.root_chord_percent = 0.070
segment.thickness_to_chord = .11
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
wing.Segments.append(segment)
# control surfaces -------------------------------------------
flap = SUAVE.Components.Wings.Control_Surfaces.Flap()
flap.tag = 'flap'
flap.span_fraction_start = 0.11
flap.span_fraction_end = 0.85
flap.deflection = 0.0 * Units.deg
flap.chord_fraction = 0.28
flap.configuration_type = 'double_slotted'
wing.append_control_surface(flap)
slat = SUAVE.Components.Wings.Control_Surfaces.Slat()
slat.tag = 'slat'
slat.span_fraction_start = 0.324
slat.span_fraction_end = 0.963
slat.deflection = 1.0 * Units.deg
slat.chord_fraction = 0.1
wing.append_control_surface(slat)
wing = wing_planform(wing)
wing.areas.exposed = 0.80 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 26.0
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.dihedral = 8.4 * Units.degrees
wing.origin = [[31, 0, 0.44]]
wing.vertical = False
wing.symmetric = True
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.dynamic_pressure_ratio = 0.90
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.areas.reference = 16.0
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 35. * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.dihedral = 0.00
wing.origin = [[30.4, 0, 1.675]]
wing.vertical = True
wing.symmetric = False
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.dynamic_pressure_ratio = 1.00
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.origin = [[0, 0, 0]]
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 30. * Units.inches
fuselage.fineness.nose = 1.28
fuselage.fineness.tail = 3.48
fuselage.lengths.nose = 6.0
fuselage.lengths.tail = 9.0
fuselage.lengths.cabin = 21.24
fuselage.lengths.total = 36.24
fuselage.lengths.fore_space = 0.
fuselage.lengths.aft_space = 0.
fuselage.width = 3.01 * Units.meters
fuselage.heights.maximum = 3.35
fuselage.heights.at_quarter_length = 3.35
fuselage.heights.at_three_quarters_length = 3.35
fuselage.heights.at_wing_root_quarter_chord = 3.35
fuselage.areas.side_projected = 239.20
fuselage.areas.wetted = 327.01
fuselage.areas.front_projected = 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.origin = [[12.0, 4.38, -2.1], [12.0, -4.38, -2.1]]
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
gt_engine.inlet_diameter = 2.0
#compute engine areas)
Amax = (np.pi / 4.) * gt_engine.nacelle_diameter**2.
Awet = 1.1 * np.pi * gt_engine.nacelle_diameter * gt_engine.engine_length # 1.1 is simple coefficient
#Assign engine area
gt_engine.areas.wetted = Awet
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air()
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 37278.0 * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
fuel = SUAVE.Components.Physical_Component()
vehicle.fuel = fuel
fuel.mass_properties.mass = vehicle.mass_properties.max_takeoff - vehicle.mass_properties.max_fuel
fuel.origin = vehicle.wings.main_wing.mass_properties.center_of_gravity
fuel.mass_properties.center_of_gravity = vehicle.wings.main_wing.aerodynamic_center
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737-800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.operating_empty = 62746.4 * Units.kilogram
vehicle.mass_properties.takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.max_zero_fuel = 62732.0 * Units.kilogram
vehicle.mass_properties.cargo = 10000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862 * Units['meters**2']
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
# used for noise calculations
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.43
wing.sweeps.quarter_chord = 17.45 * Units.deg
wing.thickness_to_chord = 0.1164
wing.taper = 0.235
wing.span_efficiency = 0.9
wing.spans.projected = 28.08 * Units.meter
wing.chords.root = 5.28 * Units.meter
wing.chords.tip = 1.26 * Units.meter
wing.chords.mean_aerodynamic = 3.81 * Units.meter
wing.areas.reference = 124.862 * Units['meters**2']
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = -2.5 * Units.degrees
wing.origin = [13.61, 0, -1.27] # meters
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30 # 30% of the chord
wing.flaps.span_start = 0.10 # 10% of the span
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_slotted'
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweeps.quarter_chord = 40 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.span_efficiency = 0.9
wing.spans.projected = 14.2 * Units.meter
wing.chords.root = 4.7 * Units.meter
wing.chords.tip = .955 * Units.meter
wing.chords.mean_aerodynamic = 8.0 * Units.meter
wing.areas.reference = 32.488 * Units['meters**2']
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [32.83, 0, 1.14] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweeps.quarter_chord = 25. * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.777 * Units.meter
wing.chords.root = 8.19 * Units.meter
wing.chords.tip = 0.95 * Units.meter
wing.chords.mean_aerodynamic = 4.0 * Units.meter
wing.areas.reference = 27.316 * Units['meters**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [28.79, 0, 1.54] # meters
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1 * Units.meter
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4 * Units.meter
fuselage.lengths.tail = 8.0 * Units.meter
fuselage.lengths.cabin = 28.85 * Units.meter
fuselage.lengths.total = 38.02 * Units.meter
fuselage.lengths.fore_space = 6. * Units.meter
fuselage.lengths.aft_space = 5. * Units.meter
fuselage.width = 3.74 * Units.meter
fuselage.heights.maximum = 3.74 * Units.meter
fuselage.effective_diameter = 3.74 * Units.meter
fuselage.areas.side_projected = 142.1948 * Units['meters**2']
fuselage.areas.wetted = 446.718 * Units['meters**2']
fuselage.areas.front_projected = 12.57 * Units['meters**2']
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
fuselage.heights.at_quarter_length = 3.74 * Units.meter
fuselage.heights.at_three_quarters_length = 3.65 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.74 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71 * Units.meter
turbofan.nacelle_diameter = 2.05 * Units.meter
turbofan.origin = [[13.72, 4.86, -1.9], [13.72, -4.86, -1.9]] # meters
#compute engine areas
turbofan.areas.wetted = 1.1 * np.pi * turbofan.nacelle_diameter * turbofan.engine_length
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.turbine_inlet_temperature = 1450 # K
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2 * 24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def engine_caluclations(altitude, bypass, mach_number, num_engine,
thrust_total):
# initialize the gas turbine network
gt_engine = Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = num_engine
gt_engine.bypass_ratio = bypass
# gt_engine.engine_length = 5.2
gt_engine.nacelle_diameter = 3.5
# set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
# add working fluid to the network
gt_engine.working_fluid = working_fluid
# Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add ram to the network
gt_engine.ram = ram
# Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.90
low_pressure_compressor.pressure_ratio = 1.5
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.90 # FIXME
high_pressure_compressor.pressure_ratio = 14
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# Component 5 :low pressure turbine
low_pressure_turbine = Turbine_saga.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.89
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# Component 5 :high pressure turbine
high_pressure_turbine = Turbine_saga.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.89
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.995
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.96
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
# add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.89
fan.pressure_ratio = 1.5
# add the fan to the network
gt_engine.fan = fan
# Component 10 : Payload power draw
generator = Generator()
generator.tag = 'generator'
generator.power_draw = 1 / gt_engine.number_of_engines
gt_engine.generator = generator
# Engine setup for noise module
gt_engine.core_nozzle_diameter = 0.92
gt_engine.fan_nozzle_diameter = 1.659
gt_engine.engine_height = 1.35 # Engine centerline heigh above the ground plane
gt_engine.exa = 1 # distance from fan face to fan exit/ fan diameter)
gt_engine.plug_diameter = 0.1 # dimater of the engine plug
gt_engine.geometry_xe = 1. # Geometry information for the installation effects function
gt_engine.geometry_ye = 1. # Geometry information for the installation effects function
gt_engine.geometry_Ce = 2. # Geometry information for the installation effects function
# Define OPR
OPR = fan.pressure_ratio * high_pressure_compressor.pressure_ratio * low_pressure_compressor.pressure_ratio
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
# total design thrust (includes all the engines)
thrust.total_design = thrust_total # should be just a pointer not a number
# add thrust to the network
gt_engine.thrust = thrust
gt_engine.OPR = OPR
# print thrust
# size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
compute_turbofan_geometry(gt_engine, None)
return gt_engine
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'E170'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 37200. * Units.kg
vehicle.mass_properties.operating_empty = 20736. * Units.kg
vehicle.mass_properties.takeoff = 37200. * Units.kg
vehicle.mass_properties.max_zero_fuel = 30140. * Units.kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 9404.0 * Units.kg
vehicle.mass_properties.max_fuel = 9428.0 * Units.kg
# vehicle.mass_properties.center_of_gravity = [11., 0., 0.]
vehicle.mass_properties.center_of_gravity = [12.925 + 0.15 * 3.194, 0., 0.]
# envelope properties
vehicle.envelope.ultimate_load = 2.5 * 1.5
vehicle.envelope.limit_load = 2.5
# basic parameters
vehicle.reference_area = 72.72 * Units['meters**2']
vehicle.passengers = 72
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.6
wing.sweeps.quarter_chord = 23.0 * Units.deg # 22.5
wing.thickness_to_chord = 0.11
wing.taper = 0.3275 #0.28
wing.span_efficiency = 0.96
wing.spans.projected = 26.0 * Units.meter
wing.chords.root = 4.2138 * Units.meter #5.428 * Units.meter
wing.chords.tip = 1.380 * Units.meter
wing.chords.mean_aerodynamic = 3.194 * Units.meter # 3.806
wing.areas.reference = 72.72 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [10.36122, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = "double_slotted"
wing.flaps.chord = 0.280
wing.dynamic_pressure_ratio = 1.0
wing.flaps.span_start = 0.13
wing.flaps.span_end = 0.75
wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 4.3
wing.sweeps.quarter_chord = 30.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.3707
wing.span_efficiency = 0.9
wing.spans.projected = 10.000 * Units.meter
wing.chords.root = 3.394 * Units.meter
wing.chords.tip = 1.258 * Units.meter
wing.chords.mean_aerodynamic = 2.4895 * Units.meter
wing.areas.reference = 23.25 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [24.6, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
# equal to E190 data
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 35 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 0.26
wing.span_efficiency = 0.90
wing.spans.projected = 5.2153 * Units.meter
wing.chords.root = 5.5779 * Units.meter
wing.chords.tip = 1.4547 * Units.meter
wing.chords.mean_aerodynamic = 3.9192 * Units.meter
wing.areas.reference = 16.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [23.9, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455 #
fuselage.fineness.nose = 2.0 #
fuselage.fineness.tail = 3.0 #
fuselage.lengths.nose = 6.00 * Units.meter
fuselage.lengths.tail = 9.00 * Units.meter
fuselage.lengths.cabin = 14.90 * Units.meter
fuselage.lengths.total = 29.90 * Units.meter
fuselage.lengths.fore_space = 0. * Units.meter
fuselage.lengths.aft_space = 0. * Units.meter
fuselage.width = 3.000 * Units.meter
fuselage.heights.maximum = 3.400 * Units.meter
fuselage.areas.side_projected = 80.000 * Units[
'meters**2'] # 197.35 * Units['meters**2']
fuselage.areas.wetted = 280.00 * Units['meters**2'] # 269.80
fuselage.areas.front_projected = 8.0110 * Units['meters**2'] # 8.0110
fuselage.effective_diameter = 3.2
fuselage.differential_pressure = 8.965 * Units.psi
fuselage.heights.at_quarter_length = 3.4 * Units.meter
fuselage.heights.at_three_quarters_length = 3.4 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.4 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.0
gt_engine.engine_length = 3.1 * Units.meter
gt_engine.nacelle_diameter = 1.64 * Units.meter
gt_engine.origin = [[9.721, 3.984, -1], [9.721, -3.984, -1]] # meters
# compute engine areas
gt_engine.areas.wetted = 1.1 * 3.14159265359 * gt_engine.nacelle_diameter * gt_engine.engine_length
#set the working fluid for the network
gt_engine.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.90
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 7.50
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# ------------------------------------------------------------------
# Component 7 - Combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.98
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.98
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# ------------------------------------------------------------------
# Component 10 - Fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.625
# add the fan to the network
gt_engine.fan = fan
# ------------------------------------------------------------------
# Component 11 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 27550.0 * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# now add weights objects
vehicle.landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.control_systems = SUAVE.Components.Physical_Component()
vehicle.electrical_systems = SUAVE.Components.Physical_Component()
vehicle.avionics = SUAVE.Components.Energy.Peripherals.Avionics()
vehicle.passenger_weights = SUAVE.Components.Physical_Component()
vehicle.furnishings = SUAVE.Components.Physical_Component()
vehicle.air_conditioner = SUAVE.Components.Physical_Component()
vehicle.fuel = SUAVE.Components.Physical_Component()
vehicle.apu = SUAVE.Components.Physical_Component()
vehicle.hydraulics = SUAVE.Components.Physical_Component()
vehicle.optionals = SUAVE.Components.Physical_Component()
vehicle.wings[
'vertical_stabilizer'].rudder = SUAVE.Components.Physical_Component()
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190AR'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties (http://www.embraercommercialaviation.com/AircraftPDF/E190_Weights.pdf)
vehicle.mass_properties.max_takeoff = 51800. # kg
vehicle.mass_properties.operating_empty = 27837. # kg
vehicle.mass_properties.takeoff = 51800. # kg
vehicle.mass_properties.max_zero_fuel = 40900. # kg
vehicle.mass_properties.max_payload = 13063. # kg
vehicle.mass_properties.max_fuel = 12971. # kg
vehicle.mass_properties.cargo = 0.0 # kg
vehicle.mass_properties.center_of_gravity = [16.8, 0, 1.6]#[[60 * Units.feet, 0, 0]] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = 92.0
wing.aspect_ratio = 8.4
wing.sweeps.quarter_chord = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.dihedral = 5.00
wing.origin = [13,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = 'double_slotted'
wing.flaps.chord = 0.28
wing.flaps.span_start = 0.11
wing.flaps.span_end = 0.85
wing = wing_planform(wing)
wing.areas.exposed = 0.80 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.span_efficiency = 1.0
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 26.0
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.dihedral = 8.00
wing.origin = [32,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.span_efficiency = 0.90
wing.dynamic_pressure_ratio = 0.90
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.areas.reference = 16.0
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 35. * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.dihedral = 0.00
wing.origin = [32,0,0]
wing.vertical = True
wing.symmetric = False
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.span_efficiency = 0.90
wing.dynamic_pressure_ratio = 1.00
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.origin = [[0,0,0]]
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0
fuselage.lengths.tail = 9.0
fuselage.lengths.cabin = 21.24
fuselage.lengths.total = 36.24
fuselage.lengths.fore_space = 0.
fuselage.lengths.aft_space = 0.
fuselage.width = 3.18
fuselage.heights.maximum = 4.18
fuselage.heights.at_quarter_length = 3.18
fuselage.heights.at_three_quarters_length = 3.18
fuselage.heights.at_wing_root_quarter_chord = 4.00
fuselage.areas.side_projected = 239.20
fuselage.areas.wetted = 327.01
fuselage.areas.front_projected = 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
#compute engine areas)
Amax = (np.pi/4.)*gt_engine.nacelle_diameter**2.
Awet = 1.1*np.pi*gt_engine.nacelle_diameter*gt_engine.engine_length # 1.1 is simple coefficient
#Assign engine areas
gt_engine.areas.wetted = Awet
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air()
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 37278.0* Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
fuel =SUAVE.Components.Physical_Component()
vehicle.fuel =fuel
fuel.mass_properties.mass =vehicle.mass_properties.max_takeoff-vehicle.mass_properties.max_fuel
fuel.origin =vehicle.wings.main_wing.mass_properties.center_of_gravity
fuel.mass_properties.center_of_gravity=vehicle.wings.main_wing.aerodynamic_center
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.operating_empty = 62746.4 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 62732.0 # kg #0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [ 15.30987849, 0. , -0.48023939]
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
#used for noise calculations
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear=landing_gear
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.1
wing.span_efficiency = 0.9
wing.spans.projected = 34.32
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.61,0,-1.27]
wing.aerodynamic_center = [0,0,0] #[3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30
wing.flaps.span_start = 0.10 # -> wing.flaps.area = 97.1112
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_slotted' # -> wing.flaps.number_slots = 2
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16 #
wing.sweeps.quarter_chord = 40 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.span_efficiency = 0.9
wing.spans.projected = 14.2 #
wing.chords.root = 4.7
wing.chords.tip = .955
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488 #
wing.areas.exposed = 199.7792 # Exposed area of the horizontal tail
wing.areas.wetted = 249.724 # Wetted area of the horizontal tail
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [32.83,0,1.14]
wing.aerodynamic_center = [0,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91 #
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.777 #
wing.chords.root = 8.19
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 27.316 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [28.79,0,1.54]
wing.aerodynamic_center = [0,0,0] #[2,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
#fuselage.number_coach_seats = 200.
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85 #44.0
fuselage.lengths.total = 38.02 #58.4
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74 #4.
fuselage.heights.maximum = 3.74 #4. #
fuselage.heights.at_quarter_length = 3.74 # Not correct
fuselage.heights.at_three_quarters_length = 3.65 # Not correct
fuselage.heights.at_wing_root_quarter_chord = 3.74 # Not correct
fuselage.areas.side_projected = 142.1948 #4.* 59.8 # Not correct
fuselage.areas.wetted = 446.718 #688.64
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74 #4.0
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# This origin is overwritten by compute_component_centers_of_gravity(base,compute_propulsor_origin=True)
turbofan.origin = [[13.72, 4.86,-1.9],[13.72, -4.86,-1.9]]
#compute engine areas
Awet = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
#Assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
turbofan.core_nozzle_diameter = 0.92
turbofan.fan_nozzle_diameter = 1.659
turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
turbofan.plug_diameter = 0.1 #dimater of the engine plug
turbofan.geometry_xe = 1. # Geometry information for the installation effects function
turbofan.geometry_ye = 1. # Geometry information for the installation effects function
turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def engine():
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
#set the working fluid for the network
gt_engine.working_fluid = SUAVE.Attributes.Gases.Air
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4: high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 52700.0* Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine,mach_number,altitude)
return gt_engine
def energy_network():
# ------------------------------------------------------------------
# Evaluation Conditions
# ------------------------------------------------------------------
# Conditions
ones_1col = np.ones([1,1])
alt = 10.0
# Setup conditions
planet = SUAVE.Attributes.Planets.Earth()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmo_data = atmosphere.compute_values(alt,0,True)
working_fluid = SUAVE.Attributes.Gases.Air()
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
# freestream conditions
conditions.freestream.altitude = ones_1col*alt
conditions.freestream.mach_number = ones_1col*0.8
conditions.freestream.pressure = ones_1col*atmo_data.pressure
conditions.freestream.temperature = ones_1col*atmo_data.temperature
conditions.freestream.density = ones_1col*atmo_data.density
conditions.freestream.dynamic_viscosity = ones_1col*atmo_data.dynamic_viscosity
conditions.freestream.gravity = ones_1col*planet.compute_gravity(alt)
conditions.freestream.isentropic_expansion_factor = ones_1col*working_fluid.compute_gamma(atmo_data.temperature,atmo_data.pressure)
conditions.freestream.Cp = ones_1col*working_fluid.compute_cp(atmo_data.temperature,atmo_data.pressure)
conditions.freestream.R = ones_1col*working_fluid.gas_specific_constant
conditions.freestream.speed_of_sound = ones_1col*atmo_data.speed_of_sound
conditions.freestream.velocity = conditions.freestream.mach_number*conditions.freestream.speed_of_sound
conditions.velocity = conditions.freestream.mach_number*conditions.freestream.speed_of_sound
conditions.q = 0.5*conditions.freestream.density*conditions.velocity**2
conditions.g0 = conditions.freestream.gravity
# propulsion conditions
conditions.propulsion.throttle = ones_1col*1.0
# ------------------------------------------------------------------
# Design/sizing conditions
# ------------------------------------------------------------------
# Conditions
ones_1col = np.ones([1,1])
alt_size = 10000.0
# Setup conditions
planet = SUAVE.Attributes.Planets.Earth()
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmo_data = atmosphere.compute_values(alt_size,0,True)
working_fluid = SUAVE.Attributes.Gases.Air()
conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
# freestream conditions
conditions_sizing.freestream.altitude = ones_1col*alt_size
conditions_sizing.freestream.mach_number = ones_1col*0.8
conditions_sizing.freestream.pressure = ones_1col*atmo_data.pressure
conditions_sizing.freestream.temperature = ones_1col*atmo_data.temperature
conditions_sizing.freestream.density = ones_1col*atmo_data.density
conditions_sizing.freestream.dynamic_viscosity = ones_1col*atmo_data.dynamic_viscosity
conditions_sizing.freestream.gravity = ones_1col*planet.compute_gravity(alt_size)
conditions_sizing.freestream.isentropic_expansion_factor = ones_1col*working_fluid.compute_gamma(atmo_data.temperature,atmo_data.pressure)
conditions_sizing.freestream.Cp = ones_1col*working_fluid.compute_cp(atmo_data.temperature,atmo_data.pressure)
conditions_sizing.freestream.R = ones_1col*working_fluid.gas_specific_constant
conditions_sizing.freestream.speed_of_sound = ones_1col*atmo_data.speed_of_sound
conditions_sizing.freestream.velocity = conditions_sizing.freestream.mach_number*conditions_sizing.freestream.speed_of_sound
conditions_sizing.velocity = conditions_sizing.freestream.mach_number*conditions_sizing.freestream.speed_of_sound
conditions_sizing.q = 0.5*conditions_sizing.freestream.density*conditions_sizing.velocity**2
conditions_sizing.g0 = conditions_sizing.freestream.gravity
# propulsion conditions
conditions_sizing.propulsion.throttle = ones_1col*1.0
state_sizing = Data()
state_sizing.numerics = Data()
state_sizing.conditions = conditions_sizing
state_off_design = Data()
state_off_design.numerics = Data()
state_off_design.conditions = conditions
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# Instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.bypass_ratio = 5.4
turbofan.number_of_engines = 2.0
turbofan.engine_length = 2.5
turbofan.nacelle_diameter = 1.580
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 - Thrust
# instantiate
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='thrust'
# setup
thrust.total_design = 42383.01818423
# add to network
turbofan.thrust = thrust
numerics = Data()
eta=1.0
#size the turbofan
turbofan_sizing(turbofan,0.8,10000.0)
print("Design thrust ",turbofan.design_thrust)
print("Sealevel static thrust ",turbofan.sealevel_static_thrust)
results_design = turbofan(state_sizing)
results_off_design = turbofan(state_off_design)
F = results_design.thrust_force_vector
mdot = results_design.vehicle_mass_rate
F_off_design = results_off_design.thrust_force_vector
mdot_off_design = results_off_design.vehicle_mass_rate
#Test the model
#Specify the expected values
expected = Data()
expected.thrust = 42360.88505056
expected.mdot = 0.76399257
#error data function
error = Data()
error.thrust_error = (F[0][0] - expected.thrust)/expected.thrust
error.mdot_error = (mdot[0][0]-expected.mdot)/expected.mdot
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1e-6)
return
def main():
vehicle = SUAVE.Vehicle()# Create the vehicle for testing
# Parameters Required
vehicle.envelope.ultimate_load = 3.5 # Ultimate load
vehicle.mass_properties.max_takeoff = 79015.8 * Units.kilograms # Maximum takeoff weight in kilograms
vehicle.mass_properties.max_zero_fuel = 79015.8 * 0.9 * Units.kilograms # Maximum zero fuel weight in kilograms
vehicle.envelope.limit_load = 1.5 # Limit Load
#Build an dsize the turbofan to get sls sthrust
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
vehicle.passengers = 170. # Number of passengers
vehicle.mass_properties.cargo = 0. * Units.kilogram # Mass of cargo
vehicle.systems.control = "fully powered" # Specify fully powered, partially powered or anything else is fully aerodynamic
vehicle.systems.accessories = "medium-range" # Specify what type of aircraft you have
vehicle.reference_area = 124.862 * Units.meter**2 # Wing gross area in square meters
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.spans.projected = 50. * Units.meter # Span in meters
wing.taper = 0.2 # Taper ratio
wing.thickness_to_chord = 0.08 # Thickness-to-chord ratio
wing.sweep = .4363323 * Units.rad # sweep angle in degrees
wing.chords.root = 15. * Units.meter # Wing root chord length
wing.chords.mean_aerodynamic = 10. * Units.meters # Length of the mean aerodynamic chord of the wing
wing.origin = [20,0,0] * Units.meters # Location of main wing from origin of the vehicle
wing.aerodynamic_center = [3,0,0] * Units.meters # Location of aerodynamic center from origin of the main wing
vehicle.append_component(wing)
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.areas.wetted = 688.64 * Units.meter**2 # Fuselage wetted area
fuselage.differential_pressure = 55960.5 * Units.pascal # Maximum differential pressure
fuselage.width = 4. * Units.meter # Width of the fuselage
fuselage.heights.maximum = 4. * Units.meter # Height of the fuselage
fuselage.lengths.total = 58.4 * Units.meter # Length of the fuselage
fuselage.number_coach_seats = 200.
vehicle.append_component(fuselage)
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 75. * Units.meters**2 # Area of the horizontal tail
wing.spans.projected = 15. * Units.meters # Span of the horizontal tail
wing.sweep = 38. * Units.deg # Sweep of the horizontal tail
wing.chords.mean_aerodynamic = 5. * Units.meters # Length of the mean aerodynamic chord of the horizontal tail
wing.thickness_to_chord = 0.07 # Thickness-to-chord ratio of the horizontal tail
wing.areas.exposed = 199.7792 # Exposed area of the horizontal tail
wing.areas.wetted = 249.724 # Wetted area of the horizontal tail
wing.origin = [45,0,0] # Location of horizontal tail from origin of the vehicle
wing.aerodynamic_center = [3,0,0] # Location of aerodynamic center from origin of the horizontal tail
vehicle.append_component(wing)
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.areas.reference = 60. * Units.meters**2 # Area of the vertical tail
wing.spans.projected = 15. * Units.meters # Span of the vertical tail
wing.thickness_to_chord = 0.07 # Thickness-to-chord ratio of the vertical tail
wing.sweep = 40. * Units.deg # Sweep of the vertical tail
wing.t_tail = "false" # Set to "yes" for a T-tail
vehicle.append_component(wing)
weight = Tube_Wing.empty(vehicle)
actual = Data()
actual.payload = 17349.9081525
actual.pax = 15036.5870655
actual.bag = 2313.321087
actual.fuel = -13680.6265874
actual.empty = 75346.5184349
actual.wing = 27694.192985
actual.fuselage = 11423.9380852
actual.propulsion = 6855.68572746
actual.landing_gear = 3160.632
actual.systems = 16655.7076511
actual.wt_furnish = 7466.1304102
actual.horizontal_tail = 2191.30720639
actual.vertical_tail = 5260.75341411
actual.rudder = 2104.30136565
error = Data()
error.payload = (actual.payload - weight.payload)/actual.payload
error.pax = (actual.pax - weight.pax)/actual.pax
error.bag = (actual.bag - weight.bag)/actual.bag
error.fuel = (actual.fuel - weight.fuel)/actual.fuel
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - weight.fuselage)/actual.fuselage
error.propulsion = (actual.propulsion - weight.propulsion)/actual.propulsion
error.landing_gear = (actual.landing_gear - weight.landing_gear)/actual.landing_gear
error.systems = (actual.systems - weight.systems)/actual.systems
error.wt_furnish = (actual.wt_furnish - weight.systems_breakdown.furnish)/actual.wt_furnish
error.horizontal_tail = (actual.horizontal_tail - weight.horizontal_tail)/actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail - weight.vertical_tail)/actual.vertical_tail
error.rudder = (actual.rudder - weight.rudder)/actual.rudder
print 'Results (kg)'
print weight
print 'Relative Errors'
print error
for k,v in error.items():
assert(np.abs(v)<0.001)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 38600. * Units.kg
vehicle.mass_properties.operating_empty = 21157. * Units.kg
vehicle.mass_properties.takeoff = 38600. * Units.kg
vehicle.mass_properties.max_zero_fuel = 30900. * Units.kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 9743.0 * Units.kg
vehicle.mass_properties.max_fuel = 9335.0 * Units.kg
vehicle.mass_properties.center_of_gravity = [14.85, 0, 0]
# envelope properties
vehicle.envelope.ultimate_load = 3.75
vehicle.envelope.limit_load = 2.50
# basic parameters
vehicle.reference_area = 72.72 * Units['meters**2']
vehicle.passengers = 72
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.6
wing.sweeps.quarter_chord = 23.0 * Units.deg # 22.5
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.span_efficiency = 1.0 #
wing.spans.projected = 26.0 * Units.meter
wing.chords.root = 5.428 * Units.meter # 5.203
wing.chords.tip = 1.380 * Units.meter # 1.460
wing.chords.mean_aerodynamic = 3.806 * Units.meter
wing.areas.reference = 72.72 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [10.36122,0,0] #
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = "double_slotted"
wing.flaps.chord = 0.280 * Units.meter #
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 4.3 #5.5
wing.sweeps.quarter_chord = 30.0 * Units.deg #34.5
wing.thickness_to_chord = 0.3707 #0.11
wing.taper = 0.11
wing.span_efficiency = 0.9 #
wing.spans.projected = 10.000 * Units.meter
wing.chords.root = 3.394 * Units.meter
wing.chords.tip = 1.258 * Units.meter
wing.chords.mean_aerodynamic = 2.4895 * Units.meter
wing.areas.reference = 23.25 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [24.6,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9 #
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
# equal to E190 data
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 35 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.span_efficiency = 0.9
wing.spans.projected = 5.270 * Units.meter
wing.chords.root = 4.70 * Units.meter
wing.chords.tip = 1.45 * Units.meter
wing.chords.mean_aerodynamic = 3.36 * Units.meter
wing.areas.reference = 16.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [23.9,0,0]
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455 #
fuselage.fineness.nose = 2.0 #
fuselage.fineness.tail = 3.0 #
fuselage.lengths.nose = 6.82 * Units.meter
fuselage.lengths.tail = 10.67 * Units.meter
fuselage.lengths.cabin = 18.23 * Units.meter
fuselage.lengths.total = 29.90 * Units.meter
fuselage.lengths.fore_space = 0. * Units.meter
fuselage.lengths.aft_space = 0. * Units.meter
fuselage.width = 2.955 * Units.meter
fuselage.heights.maximum = 3.361 * Units.meter
fuselage.areas.side_projected = 203.32 * Units['meters**2']
fuselage.areas.wetted = 277.96 * Units['meters**2']
fuselage.areas.front_projected = 31.2 * Units['meters**2'] # 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10**5 * Units.pascal
fuselage.heights.at_quarter_length = 3.35 * Units.meter
fuselage.heights.at_three_quarters_length = 3.35 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.50 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2
turbofan.bypass_ratio = 5.0
turbofan.engine_length = 3.1 * Units.meter
turbofan.nacelle_diameter = 1.64395 * Units.meter
turbofan.origin = [[9.721, 3.984,-1],[9.721,-3.984,-1]] # meters
#compute engine areas
turbofan.areas.wetted = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.9
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 10.0
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500 # K
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 52700.0 * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# ------------------------------------------------------------------
#now add weights objects
vehicle.landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.control_systems = SUAVE.Components.Physical_Component()
vehicle.electrical_systems = SUAVE.Components.Physical_Component()
vehicle.avionics = SUAVE.Components.Energy.Peripherals.Avionics()
vehicle.passenger_weights = SUAVE.Components.Physical_Component()
vehicle.furnishings = SUAVE.Components.Physical_Component()
vehicle.air_conditioner = SUAVE.Components.Physical_Component()
vehicle.fuel = SUAVE.Components.Physical_Component()
vehicle.apu = SUAVE.Components.Physical_Component()
vehicle.hydraulics = SUAVE.Components.Physical_Component()
vehicle.optionals = SUAVE.Components.Physical_Component()
vehicle.wings['vertical_stabilizer'].rudder = SUAVE.Components.Physical_Component()
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
vehicle = SUAVE.Vehicle()
#print vehicle
vehicle.mass_properties.max_zero_fuel = 238780*Units.kg
vehicle.mass_properties.max_takeoff = 833000.*Units.lbs
vehicle.design_mach_number = 0.92
vehicle.design_range = 6560 * Units.miles
vehicle.design_cruise_alt = 35000.0 * Units.ft
vehicle.envelope.limit_load = 2.5
vehicle.envelope.ultimate_load = 3.75
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "longe range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = 5500.0 * Units.feet**2
wing.spans.projected = 196.0 * Units.feet
wing.chords.mean_aerodynamic = 27.3 * Units.feet
wing.chords.root = 42.9 * Units.feet #54.5ft
wing.chords.tip = 14.7 * Units.feet
wing.sweeps.quarter_chord = 42.0 * Units.deg # Leading edge
wing.sweeps.leading_edge = 42.0 * Units.deg # Same as the quarter chord sweep (ignore why EMB)
wing.taper = wing.chords.tip / wing.chords.root
wing.aspect_ratio = wing.spans.projected**2/wing.areas.reference
wing.symmetric = True
wing.vertical = False
wing.origin = [[58.6* Units.feet ,0,3.6* Units.feet ]]
wing.aerodynamic_center = np.array([112.2*Units.feet,0.,0.])-wing.origin[0]#16.16 * Units.meters,0.,0,])
wing.dynamic_pressure_ratio = 1.0
wing.ep_alpha = 0.0
span_location_mac = compute_span_location_from_chord_length(wing, wing.chords.mean_aerodynamic)
mac_le_offset = .8*np.sin(wing.sweeps.leading_edge)*span_location_mac #assume that 80% of the chord difference is from leading edge sweep
wing.mass_properties.center_of_gravity[0] = .3*wing.chords.mean_aerodynamic+mac_le_offset
wing.thickness_to_chord = 0.14
Mach = np.array([0.198])
conditions = Data()
conditions.weights = Data()
conditions.lift_curve_slope = datcom(wing,Mach)
conditions.weights.total_mass = np.array([[vehicle.mass_properties.max_takeoff]])
wing.CL_alpha = conditions.lift_curve_slope
vehicle.reference_area = wing.areas.reference
# control surfaces -------------------------------------------
flap = SUAVE.Components.Wings.Control_Surfaces.Flap()
flap.tag = 'flap'
flap.span_fraction_start = 0.15
flap.span_fraction_end = 0.324
flap.deflection = 1.0 * Units.deg
flap.chord_fraction = 0.19
wing.append_control_surface(flap)
slat = SUAVE.Components.Wings.Control_Surfaces.Slat()
slat.tag = 'slat'
slat.span_fraction_start = 0.324
slat.span_fraction_end = 0.963
slat.deflection = 1.0 * Units.deg
slat.chord_fraction = 0.1
wing.append_control_surface(slat)
vehicle.append_component(wing)
main_wing_CLa = wing.CL_alpha
main_wing_ar = wing.aspect_ratio
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 1490.55* Units.feet**2
wing.areas.wetted = 1490.55 * Units.feet ** 2
wing.areas.exposed = 1490.55 * Units.feet ** 2
wing.spans.projected = 71.6 * Units.feet
wing.sweeps.quarter_chord = 44.0 * Units.deg # leading edge
wing.sweeps.leading_edge = 44.0 * Units.deg # Same as the quarter chord sweep (ignore why EMB)
wing.taper = 7.5/32.6
wing.aspect_ratio = wing.spans.projected**2/wing.areas.reference
wing.origin = [[187.0* Units.feet,0,0]]
wing.symmetric = True
wing.vertical = False
wing.dynamic_pressure_ratio = 0.95
wing.ep_alpha = 2.0*main_wing_CLa/np.pi/main_wing_ar
wing.aerodynamic_center = [trapezoid_ac_x(wing), 0.0, 0.0]
wing.CL_alpha = datcom(wing,Mach)
wing.thickness_to_chord = 0.1
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.spans.exposed = 32.4 * Units.feet
wing.chords.root = 38.7 * Units.feet # vertical.chords.fuselage_intersect
wing.chords.tip = 13.4 * Units.feet
wing.sweeps.quarter_chord = 50.0 * Units.deg # Leading Edge
wing.x_root_LE1 = 180.0 * Units.feet
wing.symmetric = False
wing.exposed_root_chord_offset = 13.3 * Units.feet
wing = extend_to_ref_area(wing)
wing.areas.reference = wing.extended.areas.reference
wing.areas.wetted = wing.areas.reference
wing.areas.exposed = wing.areas.reference
wing.spans.projected = wing.extended.spans.projected
wing.chords.root = 14.9612585185
dx_LE_vert = wing.extended.root_LE_change
wing.taper = 0.272993077083
wing.origin = [[wing.x_root_LE1 + dx_LE_vert,0.,0.]]
wing.aspect_ratio = (wing.spans.projected**2)/wing.areas.reference
wing.effective_aspect_ratio = 2.2
wing.symmetric = False
wing.aerodynamic_center = np.array([trapezoid_ac_x(wing),0.0,0.0])
wing.dynamic_pressure_ratio = .95
Mach = np.array([0.198])
wing.CL_alpha = 0.
wing.ep_alpha = 0.
wing.thickness_to_chord = 0.1
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.lengths.total = 229.7 * Units.feet
fuselage.areas.side_projected = 4696.16 * Units.feet**2 #used for cnbeta
fuselage.heights.maximum = 26.9 * Units.feet #used for cnbeta
fuselage.heights.at_quarter_length = 26.0 * Units.feet #used for cnbeta
fuselage.heights.at_three_quarters_length = 19.7 * Units.feet #used for cnbeta
fuselage.heights.at_wing_root_quarter_chord = 23.8 * Units.feet #used for cnbeta
fuselage.x_root_quarter_chord = 77.0 * Units.feet #used for cmalpha
fuselage.lengths.total = 229.7 * Units.feet
fuselage.width = 20.9 * Units.feet
fuselage.areas.wetted = 688.64 * Units.feet**2
fuselage.differential_pressure = 5.0e4 * Units.pascal
vehicle.append_component(fuselage)
vehicle.mass_properties.center_of_gravity=np.array([[112.2,0,0]]) * Units.feet
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 4.0
turbofan.bypass_ratio = 4.8
turbofan.engine_length = 3.934
turbofan.nacelle_diameter = 2.428
turbofan.origin = [[36.56, 22, -1.9], [27, 12, -1.9],[36.56, -22, -1.9], [27, -12, -1.9]]
# compute engine areas
Awet = 1.1 * np.pi * turbofan.nacelle_diameter * turbofan.engine_length
# Assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
# total design thrust (includes all the engines)
# picked lower range of 747-400 at https://en.wikipedia.org/wiki/Boeing_747
thrust.total_design = 4 * 276000. * Units.N # Newtons
# design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.92
isa_deviation = 0.
# Engine setup for noise module
# add to network
turbofan.thrust = thrust
# size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
#configuration.mass_properties.zero_fuel_center_of_gravity=np.array([76.5,0,0])*Units.feet #just put a number here that got the expected value output; may want to change
fuel =SUAVE.Components.Physical_Component()
fuel.origin =wing.origin
fuel.mass_properties.center_of_gravity =wing.mass_properties.center_of_gravity
fuel.mass_properties.mass =vehicle.mass_properties.max_takeoff-vehicle.mass_properties.max_zero_fuel
#find zero_fuel_center_of_gravity
cg =vehicle.mass_properties.center_of_gravity
MTOW =vehicle.mass_properties.max_takeoff
fuel_cg =fuel.origin+fuel.mass_properties.center_of_gravity
fuel_mass =fuel.mass_properties.mass
sum_moments_less_fuel=(cg*MTOW-fuel_cg*fuel_mass)
vehicle.fuel = fuel
vehicle.mass_properties.zero_fuel_center_of_gravity = sum_moments_less_fuel/vehicle.mass_properties.max_zero_fuel
return vehicle
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 52000 #79090#. # kg
vehicle.mass_properties.operating_empty = 27837. # kg
vehicle.mass_properties.takeoff = 52000 #50989. #51800. # kg
vehicle.mass_properties.max_zero_fuel = 42977. #60899.3 # kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 13063. * Units.kg
vehicle.mass_properties.max_fuel = 12971.
vehicle.mass_properties.center_of_gravity = [18. , 0, 0]
vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.00
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.4
wing.sweep = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.span_efficiency = 1.0
wing.spans.projected = 27.8
wing.chords.root = 5.203
wing.chords.tip = 1.460
wing.chords.mean_aerodynamic = 3.680
wing.areas.reference = 92.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.2,0,0] # Need to fix
# wing.aerodynamic_center = [3,0,0] # Need to fix ---> MUST INCLUDE A SIZING CALL, TO GENERATE PLANFORM
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = "double_slotted"
wing.flaps.chord = 0.280
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 5.5
wing.sweep = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
wing.spans.projected = 11.958
wing.chords.root = 3.030
wing.chords.tip = 0.883
wing.chords.mean_aerodynamic = 2.3840
wing.areas.reference = 26.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [31.,0,0] # need to fix
# wing.aerodynamic_center = [3,0,0] # Need to fix ---> MUST INCLUDE A SIZING CALL, TO GENERATE PLANFORM
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.7 #
wing.sweep = 35 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.span_efficiency = 0.9
wing.spans.projected = 5.270 #
wing.chords.root = 4.70
wing.chords.tip = 1.45
wing.chords.mean_aerodynamic = 3.36
wing.areas.reference = 16.0 #
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [29.5,0,0]
# wing.aerodynamic_center = [3,0,0] # Need to fix ---> MUST INCLUDE A SIZING CALL, TO GENERATE PLANFORM
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.origin=[0,0,0]
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0
fuselage.lengths.tail = 9.0
fuselage.lengths.cabin = 21.24
fuselage.lengths.total = 36.24
fuselage.lengths.fore_space = 0.
fuselage.lengths.aft_space = 0.
fuselage.width = 3.18
fuselage.heights.maximum = 3.50
fuselage.heights.at_quarter_length = 3.35
fuselage.heights.at_three_quarters_length = 3.35
fuselage.heights.at_wing_root_quarter_chord = 3.50
fuselage.areas.side_projected = 239.20
fuselage.areas.wetted = 327.01
fuselage.areas.front_projected = 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 52700.0* Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
#now add weights objects
landing_gear=SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.landing_gear=landing_gear
control_systems=SUAVE.Components.Physical_Component()
vehicle.control_systems=control_systems
electrical_systems=SUAVE.Components.Physical_Component()
vehicle.electrical_systems=electrical_systems
avionics=SUAVE.Components.Energy.Peripherals.Avionics()
vehicle.avionics=avionics
passengers=SUAVE.Components.Physical_Component()
vehicle.passenger_weights=passengers
furnishings=SUAVE.Components.Physical_Component()
vehicle.furnishings=furnishings
air_conditioner=SUAVE.Components.Physical_Component()
vehicle.air_conditioner=air_conditioner
fuel=SUAVE.Components.Physical_Component()
vehicle.fuel=fuel
apu=SUAVE.Components.Physical_Component()
vehicle.apu=apu
hydraulics=SUAVE.Components.Physical_Component()
vehicle.hydraulics=hydraulics
optionals=SUAVE.Components.Physical_Component()
vehicle.optionals=optionals
rudder=SUAVE.Components.Physical_Component()
vehicle.wings['vertical_stabilizer'].rudder=rudder
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 # kg
vehicle.mass_properties.operating_empty = 62746.4 # kg
vehicle.mass_properties.takeoff = 79015.8 # kg
vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [60 * Units.feet, 0,
0] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [[10**5, 0, 0],
[
0,
10**6,
0,
], [0, 0, 10**7]
] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.16
wing.span_efficiency = 0.9
wing.spans.projected = 35.66
wing.chords.root = 6.81
wing.chords.tip = 1.09
wing.chords.mean_aerodynamic = 4.235
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = -4.0 * Units.degrees
wing.origin = [20, 0, 0]
wing.aerodynamic_center = [3, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16 #
wing.sweep = 30 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.4
wing.span_efficiency = 0.9
wing.spans.projected = 14.146 #
wing.chords.root = 3.28
wing.chords.tip = 1.31
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488 #
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [50, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91 #
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.877 #
wing.chords.root = 6.60
wing.chords.tip = 1.65
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
#fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85 #44.0
fuselage.lengths.total = 38.02 #58.4
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74 #4.
fuselage.heights.maximum = 3.74 #4. #
fuselage.heights.at_quarter_length = 4. # Not correct
fuselage.heights.at_three_quarters_length = 4. # Not correct
fuselage.heights.at_wing_root_quarter_chord = 4. # Not correct
fuselage.areas.side_projected = 3.74 * 38.02 #4.* 59.8 # Not correct
fuselage.areas.wetted = 446.718 #688.64
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74 #4.0
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbo_fan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2 * 24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015. # kg
vehicle.mass_properties.takeoff = 79015. # kg
vehicle.mass_properties.max_zero_fuel = 75000.
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.payload = 16300. * Units.kilogram
vehicle.mass_properties.max_payload = 20500.
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium-range"
# ------------------------------------------------------------------
# Landing gear
# ------------------------------------------------------------------
#vehicle.landing_gear = Data()
#vehicle.landing_gear.main_tire_diameter = 1.12000 * Units.m
#vehicle.landing_gear.nose_tire_diameter = 0.6858 * Units.m
#vehicle.landing_gear.main_strut_length = 1.8 * Units.m
#vehicle.landing_gear.nose_strut_length = 1.3 * Units.m
#vehicle.landing_gear.main_units = 2 #number of main landing gear units
#vehicle.landing_gear.nose_units = 1 #number of nose landing gear
#vehicle.landing_gear.main_wheels = 2 #number of wheels on the main landing gear
#vehicle.landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
#vehicle.append_component(landing_gear)
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweep = 25. * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.16
wing.span_efficiency = 0.9
wing.spans.projected = 35.66
wing.chords.root = 6.81
wing.chords.tip = 1.09
wing.chords.mean_aerodynamic = 4.235
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = -4.0 * Units.degrees
wing.origin = [20, 0, 0]
wing.aerodynamic_center = [3, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30
wing.flaps.span_start = 0.10 # -> wing.flaps.area = 97.1112
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_sloted' # -> wing.flaps.number_slots = 2
# wing sizing
SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweep = 30 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.4
wing.span_efficiency = 0.9
wing.spans.projected = 14.146
wing.chords.root = 3.28
wing.chords.tip = 1.31
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [50, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.877
wing.chords.root = 6.60
wing.chords.tip = 1.65
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85
fuselage.lengths.total = 38.02
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74
fuselage.heights.maximum = 3.74
fuselage.heights.at_quarter_length = 3.74
fuselage.heights.at_three_quarters_length = 3.74
fuselage.heights.at_wing_root_quarter_chord = 3.74
fuselage.areas.side_projected = 142.1948
fuselage.areas.wetted = 446.718
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
#Engine setup for noise module
turbofan.core_nozzle_diameter = 0.92
turbofan.fan_nozzle_diameter = 1.659
turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
turbofan.plug_diameter = 0.1 #dimater of the engine plug
turbofan.geometry_xe = 1. # Geometry information for the installation effects function
turbofan.geometry_ye = 1. # Geometry information for the installation effects function
turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
#compute engine areas
Awet = 1.1 * np.pi * turbofan.nacelle_diameter * turbofan.engine_length
#assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# for noise
fan.rotation = 1940 #(Need to be calculated based on the thrust level)
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2 * 24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 51800.0 * Units.kg
vehicle.mass_properties.operating_empty = 29100.0 * Units.kg
vehicle.mass_properties.takeoff = 51800.0 * Units.kg
vehicle.mass_properties.max_zero_fuel = 45600.0 * Units.kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 11786. * Units.kg
vehicle.mass_properties.max_fuel = 12970. * Units.kg
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.00
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.4
wing.sweeps.quarter_chord = 22.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.16
wing.span_efficiency = 1.0
wing.spans.projected = 27.8 * Units.meter
wing.chords.root = 5.7057 * Units.meter
wing.chords.tip = 0.9129 * Units.meter
wing.chords.mean_aerodynamic = 3.8878 * Units.meter
wing.areas.reference = 92.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [20.,0,0] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
wing.spans.projected = 11.958 * Units.meter
wing.chords.root = 3.9175 * Units.meter
wing.chords.tip = 0.4309 * Units.meter
wing.chords.mean_aerodynamic = 2.6401 * Units.meter
wing.areas.reference = 26.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [50,0,0] # meters
wing.aerodynamic_center = [2,0,0] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 0.10
wing.span_efficiency = 0.9
wing.spans.projected = 5.2153 * Units.meter
wing.chords.root = 5.5779 * Units.meter
wing.chords.tip = 0.5577 * Units.meter
wing.chords.mean_aerodynamic = 3.7524 * Units.meter
wing.areas.reference = 16.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50,0,0] # meters
wing.aerodynamic_center = [2,0,0] # meters
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455 * Units.meters
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0 * Units.meter
fuselage.lengths.tail = 9.0 * Units.meter
fuselage.lengths.cabin = 21.24 * Units.meter
fuselage.lengths.total = 36.24 * Units.meter
fuselage.lengths.fore_space = 0. * Units.meter
fuselage.lengths.aft_space = 0. * Units.meter
fuselage.width = 3.0 * Units.meter
fuselage.heights.maximum = 3.4 * Units.meter
fuselage.heights.at_quarter_length = 3.4 * Units.meter
fuselage.heights.at_three_quarters_length = 3.4 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.4 * Units.meter
fuselage.areas.side_projected = 239.20 * Units['meters**2']
fuselage.areas.wetted = 327.01 * Units['meters**2']
fuselage.areas.front_projected = 8.0110 * Units['meters**2']
fuselage.effective_diameter = 3.2 * Units.meter
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
# set the working fluid for the network
gt_engine.working_fluid = SUAVE.Attributes.Gases.Air()
# Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add ram to the network
gt_engine.ram = ram
# Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.99
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.99
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.99
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
# add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.98
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add the fan to the network
gt_engine.fan = fan
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
# total design thrust (includes all the engines)
thrust.total_design = 37278.0* Units.N #Newtons
# design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
# size the turbofan
turbofan_sizing(gt_engine,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def simple_sizing(nexus):
configs = nexus.vehicle_configurations
base = configs.base
# find conditions
air_speed = nexus.missions.base.segments['cruise_2'].air_speed
altitude = 18.5 * Units.km #nexus.missions.base.segments['climb_8'].altitude_end #FIXME
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude)
freestream0 = atmosphere.compute_values(6000. * Units.ft) # cabin altitude
diff_pressure = np.max(freestream0.pressure - freestream.pressure, 0)
fuselage = base.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
# now size engine
mach_number = air_speed / freestream.speed_of_sound
# now add to freestream data object
freestream.velocity = air_speed
freestream.mach_number = mach_number
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics() # assign conditions in form for propulsor sizing
conditions.freestream = freestream
# conditions.weights.vehicle_mass_rate = -200 * Units['kg/s']
for config in configs:
config.wings.horizontal_stabilizer.areas.reference = (26.0 / 92.0) * config.wings.main_wing.areas.reference
for wing in config.wings:
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
fuselage = config.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
turbofan_sizing(config.propulsors['turbofan'], mach_number, altitude)
compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
# engine_length, nacelle_diameter, areas.wette
# diff the new data
config.store_diff()
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
landing = nexus.vehicle_configurations.landing
landing_conditions = Data()
landing_conditions.freestream = Data()
# landing weight
# landing.mass_properties.landing = 0.85 * config.mass_properties.takeoff
# Landing CL_max
altitude = nexus.missions.base.segments[-1].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
landing_conditions.freestream.velocity = nexus.missions.base.segments['descent_final'].air_speed
landing_conditions.freestream.density = rho
landing_conditions.freestream.dynamic_viscosity = mu / rho
CL_max_landing, CDi = compute_max_lift_coeff(landing, landing_conditions)
landing.maximum_lift_coefficient = CL_max_landing
# diff the new data
landing.store_diff()
# Takeoff CL_max
takeoff = nexus.vehicle_configurations.takeoff
takeoff_conditions = Data()
takeoff_conditions.freestream = Data()
altitude = nexus.missions.base.airport.altitude
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
takeoff_conditions.freestream.velocity = nexus.missions.base.segments.climb_1.air_speed
takeoff_conditions.freestream.density = rho
takeoff_conditions.freestream.dynamic_viscosity = mu / rho
max_CL_takeoff, CDi = compute_max_lift_coeff(takeoff, takeoff_conditions)
takeoff.maximum_lift_coefficient = max_CL_takeoff
takeoff.store_diff()
# Base config CL_max
base = nexus.vehicle_configurations.base
base_conditions = Data()
base_conditions.freestream = Data()
altitude = nexus.missions.base.airport.altitude
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
base_conditions.freestream.velocity = nexus.missions.base.segments.climb_1.air_speed
base_conditions.freestream.density = rho
base_conditions.freestream.dynamic_viscosity = mu / rho
max_CL_base, CDi = compute_max_lift_coeff(base, base_conditions)
base.maximum_lift_coefficient = max_CL_base
base.store_diff()
# done!
return nexus
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737-800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.operating_empty = 62746.4 * Units.kilogram
vehicle.mass_properties.takeoff = 79015.8 * Units.kilogram
vehicle.mass_properties.max_zero_fuel = 62732.0 * Units.kilogram
vehicle.mass_properties.cargo = 10000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862 * Units['meters**2']
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
# used for noise calculations
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.1
wing.taper = 0.1
wing.span_efficiency = 0.9
wing.spans.projected = 34.32 * Units.meter
wing.chords.root = 7.760 * Units.meter
wing.chords.tip = 0.782 * Units.meter
wing.chords.mean_aerodynamic = 4.235 * Units.meter
wing.areas.reference = 124.862 * Units['meters**2']
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.61,0,-1.27] # meters
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30 # 30% of the chord
wing.flaps.span_start = 0.10 # 10% of the span
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_slotted'
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweeps.quarter_chord = 40 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.2
wing.span_efficiency = 0.9
wing.spans.projected = 14.2 * Units.meter
wing.chords.root = 4.7 * Units.meter
wing.chords.tip = .955 * Units.meter
wing.chords.mean_aerodynamic = 8.0 * Units.meter
wing.areas.reference = 32.488 * Units['meters**2']
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [32.83,0,1.14] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweeps.quarter_chord = 25. * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.777 * Units.meter
wing.chords.root = 8.19 * Units.meter
wing.chords.tip = 0.95 * Units.meter
wing.chords.mean_aerodynamic = 4.0 * Units.meter
wing.areas.reference = 27.316 * Units['meters**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [28.79,0,1.54] # meters
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1 * Units.meter
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4 * Units.meter
fuselage.lengths.tail = 8.0 * Units.meter
fuselage.lengths.cabin = 28.85 * Units.meter
fuselage.lengths.total = 38.02 * Units.meter
fuselage.lengths.fore_space = 6. * Units.meter
fuselage.lengths.aft_space = 5. * Units.meter
fuselage.width = 3.74 * Units.meter
fuselage.heights.maximum = 3.74 * Units.meter
fuselage.effective_diameter = 3.74 * Units.meter
fuselage.areas.side_projected = 142.1948 * Units['meters**2']
fuselage.areas.wetted = 446.718 * Units['meters**2']
fuselage.areas.front_projected = 12.57 * Units['meters**2']
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
fuselage.heights.at_quarter_length = 3.74 * Units.meter
fuselage.heights.at_three_quarters_length = 3.65 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.74 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71 * Units.meter
turbofan.nacelle_diameter = 2.05 * Units.meter
turbofan.origin = [[13.72, 4.86,-1.9],[13.72, -4.86,-1.9]] # meters
#compute engine areas
turbofan.areas.wetted = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.turbine_inlet_temperature = 1450 # K
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
#Engine setup for noise module
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network turbofan to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def simple_sizing(nexus):
configs = nexus.vehicle_configurations
#find conditions
air_speed = nexus.missions.base.segments['cruise'].air_speed
altitude = nexus.missions.base.segments['climb_5'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude)
#now size engine
mach_number = air_speed/freestream.speed_of_sound
#now add to freestream data object
freestream.velocity = air_speed
freestream.mach_number = mach_number
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics() #assign conditions in form for propulsor sizing
conditions.freestream = freestream
HT_volume = 1.42542 * Units.less # E170
VT_volume = 0.11458 * Units.less # E170
lht = 14.24 * Units.m
lvt = 13.54 * Units.m
for config in configs:
wing_planform(config.wings.main_wing)
config.wings.horizontal_stabilizer.areas.reference = (HT_volume/lht)*(config.wings.main_wing.areas.reference *
3.194)
config.wings.vertical_stabilizer.areas.reference = (VT_volume/lvt)*(config.wings.main_wing.areas.reference *
26.0)
SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_fuel_volume(config.wings.main_wing)
nexus.summary.available_fuel = config.wings.main_wing.fuel_volume * 803.0 * 1.0197
for wing in config.wings:
wing_planform(wing)
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
turbofan_sizing(config.propulsors['turbofan'], mach_number=mach_number, altitude=altitude)
compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
config.propulsors['turbofan'].nacelle_diameter = config.propulsors['turbofan'].nacelle_diameter * 1.1462135
config.propulsors['turbofan'].engine_length = config.propulsors['turbofan'].engine_length * 1.24868
config.propulsors['turbofan'].areas.wetted = 1.1*np.pi * (config.propulsors['turbofan'].engine_length *
config.propulsors['turbofan'].nacelle_diameter)
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
landing = nexus.vehicle_configurations.landing
landing_conditions = Data()
landing_conditions.freestream = Data()
# landing weight
landing.mass_properties.landing = 0.863 * config.mass_properties.takeoff
# Landing CL_max
altitude = nexus.missions.base.segments[-1].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream_landing = atmosphere.compute_values(altitude)
landing_conditions.freestream.velocity = nexus.missions.base.segments['descent_3'].air_speed
landing_conditions.freestream.density = freestream_landing.density
landing_conditions.freestream.dynamic_viscosity = freestream_landing.dynamic_viscosity
CL_max_landing,CDi = compute_max_lift_coeff(landing, landing_conditions)
landing.maximum_lift_coefficient = CL_max_landing
#Takeoff CL_max
takeoff = nexus.vehicle_configurations.takeoff
takeoff_conditions = Data()
takeoff_conditions.freestream = Data()
altitude = nexus.missions.base.airport.altitude
freestream_takeoff = atmosphere.compute_values(altitude)
takeoff_conditions.freestream.velocity = nexus.missions.base.segments.climb_1.air_speed
takeoff_conditions.freestream.density = freestream_takeoff.density
takeoff_conditions.freestream.dynamic_viscosity = freestream_takeoff.dynamic_viscosity
max_CL_takeoff, CDi = compute_max_lift_coeff(takeoff, takeoff_conditions)
takeoff.maximum_lift_coefficient = max_CL_takeoff
#Base config CL_max
base = nexus.vehicle_configurations.base
base_conditions = Data()
base_conditions.freestream = takeoff_conditions.freestream
max_CL_base, CDi = compute_max_lift_coeff(base, base_conditions)
base.maximum_lift_coefficient = max_CL_base
return nexus
def main():
vehicle = SUAVE.Vehicle()# Create the vehicle for testing
# Parameters Required
vehicle.envelope.ultimate_load = 3.5 # Ultimate load
vehicle.mass_properties.max_takeoff = 79015.8 * Units.kilograms # Maximum takeoff weight in kilograms
vehicle.mass_properties.max_zero_fuel = 79015.8 * 0.9 * Units.kilograms # Maximum zero fuel weight in kilograms
vehicle.envelope.limit_load = 1.5 # Limit Load
#Build an dsize the turbofan to get sls sthrust
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
vehicle.passengers = 170. # Number of passengers
vehicle.mass_properties.cargo = 0. * Units.kilogram # Mass of cargo
vehicle.systems.control = "fully powered" # Specify fully powered, partially powered or anything else is fully aerodynamic
vehicle.systems.accessories = "medium-range" # Specify what type of aircraft you have
vehicle.reference_area = 124.862 * Units.meter**2 # Wing gross area in square meters
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.spans.projected = 50. * Units.meter # Span in meters
wing.taper = 0.2 # Taper ratio
wing.thickness_to_chord = 0.08 # Thickness-to-chord ratio
wing.sweeps.quarter_chord = .4363323 * Units.rad # sweep angle in degrees
wing.chords.root = 15. * Units.meter # Wing root chord length
wing.chords.mean_aerodynamic = 10. * Units.meters # Length of the mean aerodynamic chord of the wing
wing.origin = [20,0,0] * Units.meters # Location of main wing from origin of the vehicle
wing.aerodynamic_center = [3,0,0] * Units.meters # Location of aerodynamic center from origin of the main wing
vehicle.append_component(wing)
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.areas.wetted = 688.64 * Units.meter**2 # Fuselage wetted area
fuselage.differential_pressure = 55960.5 * Units.pascal # Maximum differential pressure
fuselage.width = 4. * Units.meter # Width of the fuselage
fuselage.heights.maximum = 4. * Units.meter # Height of the fuselage
fuselage.lengths.total = 58.4 * Units.meter # Length of the fuselage
fuselage.number_coach_seats = 200.
vehicle.append_component(fuselage)
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 75. * Units.meters**2 # Area of the horizontal tail
wing.spans.projected = 15. * Units.meters # Span of the horizontal tail
wing.sweeps.quarter_chord = 38. * Units.deg # Sweep of the horizontal tail
wing.chords.mean_aerodynamic = 5. * Units.meters # Length of the mean aerodynamic chord of the horizontal tail
wing.thickness_to_chord = 0.07 # Thickness-to-chord ratio of the horizontal tail
wing.areas.exposed = 199.7792 # Exposed area of the horizontal tail
wing.areas.wetted = 249.724 # Wetted area of the horizontal tail
wing.origin = [45,0,0] # Location of horizontal tail from origin of the vehicle
wing.aerodynamic_center = [3,0,0] # Location of aerodynamic center from origin of the horizontal tail
vehicle.append_component(wing)
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.areas.reference = 60. * Units.meters**2 # Area of the vertical tail
wing.spans.projected = 15. * Units.meters # Span of the vertical tail
wing.thickness_to_chord = 0.07 # Thickness-to-chord ratio of the vertical tail
wing.sweeps.quarter_chord = 40. * Units.deg # Sweep of the vertical tail
wing.t_tail = "false" # Set to "yes" for a T-tail
vehicle.append_component(wing)
weight = Tube_Wing.empty(vehicle)
actual = Data()
actual.payload = 17349.9081525
actual.pax = 15036.5870655
actual.bag = 2313.321087
actual.fuel = -13680.6265874
actual.empty = 75346.5184349
actual.wing = 27694.192985
actual.fuselage = 11423.9380852
actual.propulsion = 6855.68572746
actual.landing_gear = 3160.632
actual.systems = 16655.7076511
actual.wt_furnish = 7466.1304102
actual.horizontal_tail = 2191.30720639
actual.vertical_tail = 5260.75341411
actual.rudder = 2104.30136565
error = Data()
error.payload = (actual.payload - weight.payload)/actual.payload
error.pax = (actual.pax - weight.pax)/actual.pax
error.bag = (actual.bag - weight.bag)/actual.bag
error.fuel = (actual.fuel - weight.fuel)/actual.fuel
error.empty = (actual.empty - weight.empty)/actual.empty
error.wing = (actual.wing - weight.wing)/actual.wing
error.fuselage = (actual.fuselage - weight.fuselage)/actual.fuselage
error.propulsion = (actual.propulsion - weight.propulsion)/actual.propulsion
error.landing_gear = (actual.landing_gear - weight.landing_gear)/actual.landing_gear
error.systems = (actual.systems - weight.systems)/actual.systems
error.wt_furnish = (actual.wt_furnish - weight.systems_breakdown.furnish)/actual.wt_furnish
error.horizontal_tail = (actual.horizontal_tail - weight.horizontal_tail)/actual.horizontal_tail
error.vertical_tail = (actual.vertical_tail - weight.vertical_tail)/actual.vertical_tail
error.rudder = (actual.rudder - weight.rudder)/actual.rudder
print 'Results (kg)'
print weight
print 'Relative Errors'
print error
for k,v in error.items():
assert(np.abs(v)<0.001)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 51800.0 * Units.kg
vehicle.mass_properties.operating_empty = 29100.0 * Units.kg
vehicle.mass_properties.takeoff = 51800.0 * Units.kg
vehicle.mass_properties.max_zero_fuel = 45600.0 * Units.kg
vehicle.mass_properties.cargo = 0.0 * Units.kg
vehicle.mass_properties.max_payload = 11786. * Units.kg
vehicle.mass_properties.max_fuel = 12970. * Units.kg
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.00
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.4
wing.sweeps.quarter_chord = 22.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.16
wing.span_efficiency = 1.0
wing.spans.projected = 27.8 * Units.meter
wing.chords.root = 5.7057 * Units.meter
wing.chords.tip = 0.9129 * Units.meter
wing.chords.mean_aerodynamic = 3.8878 * Units.meter
wing.areas.reference = 92.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [20., 0, 0] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
wing.spans.projected = 11.958 * Units.meter
wing.chords.root = 3.9175 * Units.meter
wing.chords.tip = 0.4309 * Units.meter
wing.chords.mean_aerodynamic = 2.6401 * Units.meter
wing.areas.reference = 26.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [50, 0, 0] # meters
wing.aerodynamic_center = [2, 0, 0] # meters
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 25 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 0.10
wing.span_efficiency = 0.9
wing.spans.projected = 5.2153 * Units.meter
wing.chords.root = 5.5779 * Units.meter
wing.chords.tip = 0.5577 * Units.meter
wing.chords.mean_aerodynamic = 3.7524 * Units.meter
wing.areas.reference = 16.0 * Units['meters**2']
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50, 0, 0] # meters
wing.aerodynamic_center = [2, 0, 0] # meters
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455 * Units.meters
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0 * Units.meter
fuselage.lengths.tail = 9.0 * Units.meter
fuselage.lengths.cabin = 21.24 * Units.meter
fuselage.lengths.total = 36.24 * Units.meter
fuselage.lengths.fore_space = 0. * Units.meter
fuselage.lengths.aft_space = 0. * Units.meter
fuselage.width = 3.0 * Units.meter
fuselage.heights.maximum = 3.4 * Units.meter
fuselage.heights.at_quarter_length = 3.4 * Units.meter
fuselage.heights.at_three_quarters_length = 3.4 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.4 * Units.meter
fuselage.areas.side_projected = 239.20 * Units['meters**2']
fuselage.areas.wetted = 327.01 * Units['meters**2']
fuselage.areas.front_projected = 8.0110 * Units['meters**2']
fuselage.effective_diameter = 3.2 * Units.meter
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
# initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
# set the working fluid for the network
gt_engine.working_fluid = SUAVE.Attributes.Gases.Air()
# Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add ram to the network
gt_engine.ram = ram
# Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.99
# add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
# Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
# add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
# Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
# add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
# Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag = 'lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.99
# add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
# Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag = 'hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.99
# add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
# Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add the combustor to the network
gt_engine.combustor = combustor
# Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
# add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
# Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.98
# add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
# Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# add the fan to the network
gt_engine.fan = fan
# Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag = 'compute_thrust'
# total design thrust (includes all the engines)
thrust.total_design = 37278.0 * Units.N #Newtons
# design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
# size the turbofan
turbofan_sizing(gt_engine, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Boeing_737800'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 79015. # kg
vehicle.mass_properties.takeoff = 79015. # kg
vehicle.mass_properties.max_zero_fuel = 75000.
vehicle.mass_properties.cargo = 10000. * Units.kilogram
vehicle.mass_properties.payload = 16300. * Units.kilogram
vehicle.mass_properties.max_payload = 20500.
# envelope properties
vehicle.envelope.ultimate_load = 2.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 124.862
vehicle.passengers = 170
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium-range"
# ------------------------------------------------------------------
# Landing gear
# ------------------------------------------------------------------
#vehicle.landing_gear = Data()
#vehicle.landing_gear.main_tire_diameter = 1.12000 * Units.m
#vehicle.landing_gear.nose_tire_diameter = 0.6858 * Units.m
#vehicle.landing_gear.main_strut_length = 1.8 * Units.m
#vehicle.landing_gear.nose_strut_length = 1.3 * Units.m
#vehicle.landing_gear.main_units = 2 #number of main landing gear units
#vehicle.landing_gear.nose_units = 1 #number of nose landing gear
#vehicle.landing_gear.main_wheels = 2 #number of wheels on the main landing gear
#vehicle.landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 1.12000 * Units.m
landing_gear.nose_tire_diameter = 0.6858 * Units.m
landing_gear.main_strut_length = 1.8 * Units.m
landing_gear.nose_strut_length = 1.3 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 2 #number of wheels on the main landing gear
landing_gear.nose_wheels = 2 #number of wheels on the nose landing gear
vehicle.landing_gear=landing_gear
#vehicle.append_component(landing_gear)
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.18
wing.sweep = 25. * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.16
wing.span_efficiency = 0.9
wing.spans.projected = 35.66
wing.chords.root = 6.81
wing.chords.tip = 1.09
wing.chords.mean_aerodynamic = 4.235
wing.areas.reference = 124.862
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = -4.0 * Units.degrees
wing.origin = [20,0,0]
wing.aerodynamic_center = [3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.30
wing.flaps.span_start = 0.10 # -> wing.flaps.area = 97.1112
wing.flaps.span_end = 0.75
wing.flaps.type = 'double_sloted' # -> wing.flaps.number_slots = 2
# wing sizing
SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 6.16
wing.sweep = 30 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.4
wing.span_efficiency = 0.9
wing.spans.projected = 14.146
wing.chords.root = 3.28
wing.chords.tip = 1.31
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [50,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.91
wing.sweep = 25 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.25
wing.span_efficiency = 0.9
wing.spans.projected = 7.877
wing.chords.root = 6.60
wing.chords.tip = 1.65
wing.chords.mean_aerodynamic = 8.0
wing.areas.reference = 32.488
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [50,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 6
fuselage.seat_pitch = 1
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 6.4
fuselage.lengths.tail = 8.0
fuselage.lengths.cabin = 28.85
fuselage.lengths.total = 38.02
fuselage.lengths.fore_space = 6.
fuselage.lengths.aft_space = 5.
fuselage.width = 3.74
fuselage.heights.maximum = 3.74
fuselage.heights.at_quarter_length = 3.74
fuselage.heights.at_three_quarters_length = 3.74
fuselage.heights.at_wing_root_quarter_chord = 3.74
fuselage.areas.side_projected = 142.1948
fuselage.areas.wetted = 446.718
fuselage.areas.front_projected = 12.57
fuselage.effective_diameter = 3.74
fuselage.differential_pressure = 5.0e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbofan = SUAVE.Components.Energy.Networks.Turbofan()
turbofan.tag = 'turbofan'
# setup
turbofan.number_of_engines = 2.0
turbofan.bypass_ratio = 5.4
turbofan.engine_length = 2.71
turbofan.nacelle_diameter = 2.05
#Engine setup for noise module
turbofan.core_nozzle_diameter = 0.92
turbofan.fan_nozzle_diameter = 1.659
turbofan.engine_height = 0.5 #Engine centerline heigh above the ground plane
turbofan.exa = 1 #distance from fan face to fan exit/ fan diameter)
turbofan.plug_diameter = 0.1 #dimater of the engine plug
turbofan.geometry_xe = 1. # Geometry information for the installation effects function
turbofan.geometry_ye = 1. # Geometry information for the installation effects function
turbofan.geometry_Ce = 2. # Geometry information for the installation effects function
#compute engine areas
Awet = 1.1*np.pi*turbofan.nacelle_diameter*turbofan.engine_length
#assign engine areas
turbofan.areas.wetted = Awet
# working fluid
turbofan.working_fluid = SUAVE.Attributes.Gases.Air()
# ------------------------------------------------------------------
# Component 1 - Ram
# to convert freestream static to stagnation quantities
# instantiate
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
# add to the network
turbofan.append(ram)
# ------------------------------------------------------------------
# Component 2 - Inlet Nozzle
# instantiate
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet_nozzle'
# setup
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
# add to network
turbofan.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 1.14
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.91
compressor.pressure_ratio = 13.415
# add to network
turbofan.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 0.99
turbine.polytropic_efficiency = 0.93
# add to network
turbofan.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1450
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbofan.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Fan Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'fan_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbofan.append(nozzle)
# ------------------------------------------------------------------
# Component 10 - Fan
# instantiate
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
# setup
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
# for noise
fan.rotation = 1940 #(Need to be calculated based on the thrust level)
# add to network
turbofan.append(fan)
# ------------------------------------------------------------------
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 2*24000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add to network
turbofan.thrust = thrust
#size the turbofan
turbofan_sizing(turbofan,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbofan)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def simple_sizing(nexus):
configs = nexus.vehicle_configurations
base = configs.base
#find conditions
air_speed = nexus.missions.base.segments['cruise'].air_speed
altitude = nexus.missions.base.segments['climb_5'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude)
freestream0 = atmosphere.compute_values(6000. * Units.ft) #cabin altitude
diff_pressure = np.max(freestream0.pressure - freestream.pressure, 0)
fuselage = base.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
#now size engine
mach_number = air_speed / freestream.speed_of_sound
#now add to freestream data object
freestream.velocity = air_speed
freestream.mach_number = mach_number
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
) #assign conditions in form for propulsor sizing
conditions.freestream = freestream
for config in configs:
config.wings.horizontal_stabilizer.areas.reference = (
26.0 / 92.0) * config.wings.main_wing.areas.reference
for wing in config.wings:
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(
wing)
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
fuselage = config.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
turbofan_sizing(config.propulsors['turbofan'], mach_number, altitude)
compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
# diff the new data
#config.store_diff()
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
landing = nexus.vehicle_configurations.landing
landing_conditions = Data()
landing_conditions.freestream = Data()
# landing weight
landing.mass_properties.landing = 0.85 * config.mass_properties.takeoff
# Landing CL_max
altitude = nexus.missions.base.segments[-1].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
landing_conditions.freestream.velocity = nexus.missions.base.segments[
'descent_3'].air_speed
landing_conditions.freestream.density = rho
landing_conditions.freestream.dynamic_viscosity = mu / rho
CL_max_landing, CDi = compute_max_lift_coeff(landing, landing_conditions)
landing.maximum_lift_coefficient = CL_max_landing
# diff the new data
#landing.store_diff()
#Takeoff CL_max
takeoff = nexus.vehicle_configurations.takeoff
takeoff_conditions = Data()
takeoff_conditions.freestream = Data()
altitude = nexus.missions.base.airport.altitude
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
takeoff_conditions.freestream.velocity = nexus.missions.base.segments.climb_1.air_speed
takeoff_conditions.freestream.density = rho
takeoff_conditions.freestream.dynamic_viscosity = mu / rho
max_CL_takeoff, CDi = compute_max_lift_coeff(takeoff, takeoff_conditions)
takeoff.maximum_lift_coefficient = max_CL_takeoff
#takeoff.store_diff()
#Base config CL_max
base = nexus.vehicle_configurations.base
base_conditions = Data()
base_conditions.freestream = Data()
altitude = nexus.missions.base.airport.altitude
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
p, T, rho, a, mu = atmosphere.compute_values(altitude)
base_conditions.freestream.velocity = nexus.missions.base.segments.climb_1.air_speed
base_conditions.freestream.density = rho
base_conditions.freestream.dynamic_viscosity = mu / rho
max_CL_base, CDi = compute_max_lift_coeff(base, base_conditions)
base.maximum_lift_coefficient = max_CL_base
#base.store_diff()
# done!
return nexus
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'EMBRAER E190AR'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 51800.0 # kg
vehicle.mass_properties.operating_empty = 29100.0 # kg
vehicle.mass_properties.takeoff = 51800.0 # kg
## vehicle.mass_properties.max_zero_fuel = 0.9 * vehicle.mass_properties.max_takeoff
vehicle.mass_properties.cargo = 0. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [60 * Units.feet, 0, 0] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.0
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 8.4
wing.sweep = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.span_efficiency = 1.0
## wing.spans.projected = 27.8
##
## wing.chords.root = 5.203
## wing.chords.tip = 1.460
## wing.chords.mean_aerodynamic = 3.680
wing.areas.reference = 92.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [13.2,0,0] # Need to fix
## wing.aerodynamic_center = [3,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = "double_slotted"
wing.flaps.chord = 0.280
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 5.5
wing.sweep = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.span_efficiency = 0.9
## wing.spans.projected = 11.958
##
## wing.chords.root = 3.030
## wing.chords.tip = 0.883
## wing.chords.mean_aerodynamic = 2.3840
wing.areas.reference = 26.0
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [31.,0,0] # need to fix
## wing.aerodynamic_center = [2,0,0]
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.7 #
wing.sweep = 35 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.span_efficiency = 0.9
## wing.spans.projected = 5.270 #
##
## wing.chords.root = 4.70
## wing.chords.tip = 1.45
## wing.chords.mean_aerodynamic = 3.36
wing.areas.reference = 16.0 #
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [29.5,0,0]
## wing.aerodynamic_center = [2,0,0]
wing.vertical = True
wing.symmetric = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
size_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
gt_engine.position[1] = 4.50
#compute engine areas
Awet = 1.1*np.pi*gt_engine.nacelle_diameter*gt_engine.engine_length
#assign engine areas
gt_engine.areas.wetted = Awet
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98 # turbofan.fan_nozzle_pressure_ratio = 0.98 #0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 37278.0* Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
#create conditions object for sizing the turbofan
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
conditions = atmosphere.compute_values(altitude)
turbofan_sizing(gt_engine,mach_number,altitude)
compute_turbofan_geometry(gt_engine, conditions)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
