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 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 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 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 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