def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Concorde'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 185000. * Units.kilogram
vehicle.mass_properties.operating_empty = 78700. * Units.kilogram
vehicle.mass_properties.takeoff = 185000. * Units.kilogram
vehicle.mass_properties.cargo = 1000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 358.25 * Units['meter**2']
vehicle.passengers = 100
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.83
wing.sweeps.quarter_chord = 59.5 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.
wing.span_efficiency = .8
wing.spans.projected = 25.6 * Units.meter
wing.chords.root = 33.8 * Units.meter
wing.total_length = 33.8 * Units.meter
wing.chords.tip = 1.1 * Units.meter
wing.chords.mean_aerodynamic = 18.4 * Units.meter
wing.areas.reference = 358.25 * Units['meter**2']
wing.areas.wetted = 653. - 12.*2.4*2 # 2.4 is engine area on one side
wing.areas.exposed = 326.5 * Units['meter**2']
wing.areas.affected = .6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [14,0,-.8] # meters
wing.aerodynamic_center = [35,0,0] # meters
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.vortex_lift = True
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 0.74
wing.sweeps.quarter_chord = 60 * Units.deg
wing.thickness_to_chord = 0.04
wing.taper = 0.14
wing.span_efficiency = 0.9
wing.spans.projected = 6.0 * Units.meter
wing.chords.root = 14.5 * Units.meter
wing.total_length = 14.5 * Units.meter
wing.chords.tip = 2.7 * Units.meter
wing.chords.mean_aerodynamic = 8.66 * Units.meter
wing.areas.reference = 33.91 * Units['meter**2']
wing.areas.wetted = 76. * Units['meter**2']
wing.areas.exposed = 38. * Units['meter**2']
wing.areas.affected = 33.91 * Units['meter**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [42.,0,1.] # meters
wing.aerodynamic_center = [50,0,0] # meters
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
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 = 4
fuselage.seat_pitch = 1 * Units.meter
fuselage.fineness.nose = 4.3 * Units.meter
fuselage.fineness.tail = 6.4 * Units.meter
fuselage.lengths.total = 61.66 * Units.meter
fuselage.width = 2.88 * Units.meter
fuselage.heights.maximum = 3.32 * Units.meter
fuselage.heights.maximum = 3.32 * Units.meter
fuselage.heights.at_quarter_length = 3.32 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 3.32 * Units.meter
fuselage.heights.at_three_quarters_length = 3.32 * Units.meter
fuselage.areas.wetted = 447. * Units['meter**2']
fuselage.areas.front_projected = 11.9 * Units['meter**2']
fuselage.effective_diameter = 3.1 * Units.meter
fuselage.differential_pressure = 7.4e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
# instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 4.0
turbojet.engine_length = 12.0
turbojet.nacelle_diameter = 1.3 * Units.meter
turbojet.inlet_diameter = 1.1 * Units.meter
turbojet.areas = Data()
turbojet.areas.wetted = 12.5*4.7*2. * Units['meter**2'] # 4.7 is outer perimeter on one side
turbojet.origin = [[37.,6.,-1.3],[37.,5.3,-1.3],[37.,-5.3,-1.3],[37.,-6.,-1.3]] # meters
# working fluid
turbojet.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
turbojet.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 = 1.0
# add to network
turbojet.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 = 3.1
# add to network
turbojet.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 = 5.0
# add to network
turbojet.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
turbojet.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
turbojet.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.
combustor.pressure_ratio = 1.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
#Component 9 : 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 = 4*140000. * Units.N #Newtons
# Note: Sizing builds the propulsor. It does not actually set the size of the turbojet
# design sizing conditions
altitude = 0.0*Units.ft
mach_number = 0.01
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Concorde'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 185000. # kg
vehicle.mass_properties.operating_empty = 78700. # kg
vehicle.mass_properties.takeoff = 183000. # kg, adjusted due to significant fuel burn on runway
vehicle.mass_properties.cargo = 1000. * Units.kilogram
vehicle.mass_properties.max_zero_fuel = 92000.
# envelope properties
vehicle.envelope.ultimate_load = 3.75
vehicle.envelope.limit_load = 2.5
# basic parameters
vehicle.reference_area = 358.25
vehicle.passengers = 100
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "sst"
vehicle.maximum_cross_sectional_area = 13.9
vehicle.total_length = 61.66
vehicle.design_mach_number = 2.02
vehicle.design_range = 4505 * Units.miles
vehicle.design_cruise_alt = 60000.0 * Units.ft
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.83
wing.sweeps.quarter_chord = 59.5 * Units.deg
wing.sweeps.leading_edge = 66.5 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.
wing.spans.projected = 25.6
wing.chords.root = 33.8
wing.total_length = 33.8
wing.chords.tip = 1.1
wing.chords.mean_aerodynamic = 18.4
wing.areas.reference = 358.25
wing.areas.wetted = 601.
wing.areas.exposed = 326.5
wing.areas.affected = .6 * wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[14, 0, -.8]]
wing.aerodynamic_center = [35, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.vortex_lift = True
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
wing_airfoil = SUAVE.Components.Airfoils.Airfoil()
# This airfoil is not a true Concorde airfoil
wing_airfoil.coordinate_file = '../Vehicles/Airfoils/NACA65-203.txt'
wing.append_airfoil(wing_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 33.8 / 33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 67. * Units.deg
segment.thickness_to_chord = 0.03
#segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set section 2 start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 6.15 / (
25.6 / 2) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 13.8 / 33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 48. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set section 3 start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_3'
segment.percent_span_location = 5.95 / (
25.6 / 2) + wing.Segments['section_2'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 4.4 / 33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 71. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set tip
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.1 / 33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# Fill out more segment properties automatically
wing = wing_segmented_planform(wing)
# CG locations are approximate
# Masses from http://www.concordesst.com/fuelsys.html
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_9'
fuel_tank.mass_properties.center_of_gravity = np.array([[26.5, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 11096
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_10'
fuel_tank.mass_properties.center_of_gravity = np.array([[28.7, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 11943
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_1_and_4'
fuel_tank.mass_properties.center_of_gravity = np.array([[31.0, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 4198 + 4198
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_5_and_8'
fuel_tank.mass_properties.center_of_gravity = np.array([[32.9, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 7200 + 12838
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_6_and_7'
fuel_tank.mass_properties.center_of_gravity = np.array([[37.4, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 11587 + 7405
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_5A_and_7A'
fuel_tank.mass_properties.center_of_gravity = np.array([[40.2, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 2225 + 2225
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_2_and_3'
fuel_tank.mass_properties.center_of_gravity = np.array([[40.2, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 4570 + 4570
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 0.74 #
wing.sweeps.quarter_chord = 60 * Units.deg
wing.thickness_to_chord = 0.04
wing.taper = 0.14
wing.spans.projected = 6.0 #
wing.chords.root = 14.5
wing.total_length = 14.5
wing.chords.tip = 2.7
wing.chords.mean_aerodynamic = 8.66
wing.areas.reference = 33.91 #
wing.areas.wetted = 76.
wing.areas.exposed = 38.
wing.areas.affected = 33.91
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[42., 0, 1.]]
wing.aerodynamic_center = [50, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
tail_airfoil = SUAVE.Components.Airfoils.Airfoil()
# This airfoil is not a true Concorde airfoil
tail_airfoil.coordinate_file = '../Vehicles/Airfoils/supersonic_tail.txt'
wing.append_airfoil(tail_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 14.5 / 14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 63. * Units.deg
segment.thickness_to_chord = 0.04
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# set mid section start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 2.4 / (
6.0) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 7.5 / 14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 40. * Units.deg
segment.thickness_to_chord = 0.04
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# set tip
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 2.7 / 14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.04
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# Fill out more segment properties automatically
wing = wing_segmented_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 4
fuselage.seat_pitch = 38. * Units.inches
fuselage.fineness.nose = 4.3
fuselage.fineness.tail = 6.4
fuselage.lengths.total = 61.66
fuselage.width = 2.88
fuselage.heights.maximum = 3.32 #
fuselage.heights.maximum = 3.32 #
fuselage.heights.at_quarter_length = 3.32 #
fuselage.heights.at_wing_root_quarter_chord = 3.32 #
fuselage.heights.at_three_quarters_length = 3.32 #
fuselage.areas.wetted = 442.
fuselage.areas.front_projected = 11.9
fuselage.effective_diameter = 3.1
fuselage.differential_pressure = 7.4e4 * Units.pascal # Maximum differential pressure
fuselage.OpenVSP_values = Data() # VSP uses degrees directly
fuselage.OpenVSP_values.nose = Data()
fuselage.OpenVSP_values.nose.top = Data()
fuselage.OpenVSP_values.nose.side = Data()
fuselage.OpenVSP_values.nose.top.angle = 20.0
fuselage.OpenVSP_values.nose.top.strength = 0.75
fuselage.OpenVSP_values.nose.side.angle = 20.0
fuselage.OpenVSP_values.nose.side.strength = 0.75
fuselage.OpenVSP_values.nose.TB_Sym = True
fuselage.OpenVSP_values.nose.z_pos = -.01
fuselage.OpenVSP_values.tail = Data()
fuselage.OpenVSP_values.tail.top = Data()
fuselage.OpenVSP_values.tail.side = Data()
fuselage.OpenVSP_values.tail.bottom = Data()
fuselage.OpenVSP_values.tail.top.angle = 0.0
fuselage.OpenVSP_values.tail.top.strength = 0.0
# CG locations are approximate
# Masses from http://www.concordesst.com/fuelsys.html
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_11'
fuel_tank.mass_properties.center_of_gravity = np.array([[49.8, 0, 0]])
fuel_tank.mass_properties.fuel_mass_when_full = 10415
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
fuselage.Fuel_Tanks.append(fuel_tank)
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# the nacelle
# ------------------------------------------------------------------
nacelle = SUAVE.Components.Nacelles.Nacelle()
nacelle.diameter = 1.3
nacelle.tag = 'nacelle_L1'
nacelle.origin = [[36.56, 22, -1.9]]
nacelle.length = 12.0
nacelle.inlet_diameter = 1.1
nacelle.areas.wetted = 30.
vehicle.append_component(nacelle)
nacelle_2 = deepcopy(nacelle)
nacelle_2.tag = 'nacelle_2'
nacelle_2.origin = [[37., 5.3, -1.3]]
vehicle.append_component(nacelle_2)
nacelle_3 = deepcopy(nacelle)
nacelle_3.tag = 'nacelle_3'
nacelle_3.origin = [[37., -5.3, -1.3]]
vehicle.append_component(nacelle_3)
nacelle_4 = deepcopy(nacelle)
nacelle_4.tag = 'nacelle_4'
nacelle_4.origin = [[37., -6., -1.3]]
vehicle.append_component(nacelle_4)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
# instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 4.0
turbojet.engine_length = 12.0
turbojet.nacelle_diameter = 1.3
turbojet.inlet_diameter = 1.1
turbojet.areas = Data()
turbojet.areas.wetted = 120. / turbojet.number_of_engines
turbojet.origin = [[37., 6., -1.3], [37., 5.3, -1.3], [37., -5.3, -1.3],
[37., -6., -1.3]]
# working fluid
turbojet.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
turbojet.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
inlet_nozzle.pressure_recovery = 0.94
# add to network
turbojet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.88
compressor.pressure_ratio = 3.1
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.88
compressor.pressure_ratio = 5.0
# add to network
turbojet.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 = 0.89
# add to network
turbojet.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 = 0.87
# add to network
turbojet.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.94
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1440.
combustor.pressure_ratio = 0.92
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Afterburner
# instantiate
afterburner = SUAVE.Components.Energy.Converters.Combustor()
afterburner.tag = 'afterburner'
# setup
afterburner.efficiency = 0.9
afterburner.alphac = 1.0
afterburner.turbine_inlet_temperature = 1500
afterburner.pressure_ratio = 1.0
afterburner.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(afterburner)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.pressure_recovery = 0.95
nozzle.pressure_ratio = 1.
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
#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 = 40000. * Units.lbf
# Note: Sizing builds the network. It does not actually set the size of the turbojet
#design sizing conditions
altitude = 60000.0 * Units.ft
mach_number = 2.02
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'AS2'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 52163. # kg
vehicle.mass_properties.operating_empty = 22500. # kg
vehicle.mass_properties.takeoff = 52163. # kg
vehicle.mass_properties.cargo = 1000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [26.3 * Units.feet, 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 = 125.4
vehicle.passengers = 8
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 3.63
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.7
wing.span_efficiency = 0.74
wing.spans.projected = 21.0
wing.chords.root = 12.9
wing.chords.tip = 1.0
wing.chords.mean_aerodynamic = 7.0
wing.areas.reference = 125.4
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [20, 0, 0]
wing.aerodynamic_center = [5, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 2.0 #
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.5
wing.span_efficiency = 0.74
wing.spans.projected = 7.0 #
wing.chords.root = 4.0
wing.chords.tip = 2.0
wing.chords.mean_aerodynamic = 3.3
wing.areas.reference = 24.5 #
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [46, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = False
wing.symmetric = True
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 1.3 #
wing.sweeps.quarter_chord = 45 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.5
wing.span_efficiency = 0.9
wing.spans.projected = 3.5 #
wing.chords.root = 6.0
wing.chords.tip = 3.0
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 33.9 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [40, 0, 0]
wing.aerodynamic_center = [2, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 2
fuselage.seat_pitch = 1
fuselage.fineness.nose = 4.0 # These finenesses are smaller than the real value due to limitations of existing functions
fuselage.fineness.tail = 4.0
fuselage.lengths.nose = 12.
fuselage.lengths.tail = 25.5
fuselage.lengths.cabin = 11.5
fuselage.lengths.total = 49.
fuselage.lengths.fore_space = 16.3
fuselage.lengths.aft_space = 16.3
fuselage.width = 2.35
fuselage.heights.maximum = 2.55 #
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 = 4. * 59.8 # Not correct
fuselage.areas.wetted = 615.
fuselage.areas.front_projected = 5.1
fuselage.effective_diameter = 2.4
fuselage.differential_pressure = 50**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 3.0
turbojet.engine_length = 8.0
turbojet.nacelle_diameter = 1.580
# working fluid
turbojet.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
turbojet.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
turbojet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 1.0
compressor.pressure_ratio = 5.0
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 1.0
compressor.pressure_ratio = 10.0
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 1.0
turbine.polytropic_efficiency = 1.0
# add to network
turbojet.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag = 'high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 1.0
turbine.polytropic_efficiency = 1.0
# add to network
turbojet.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 = 1500.
combustor.pressure_ratio = 1.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
#nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 1.0
nozzle.pressure_ratio = 1.0
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Divergening Nozzle
# ------------------------------------------------------------------
#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 * 15000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0 * Units.ft
mach_number = 2.02
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet, mach_number, altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup(source_ratio=1.):
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Concorde'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 185000. # kg
vehicle.mass_properties.operating_empty = 78700. # kg
vehicle.mass_properties.takeoff = 185000. # kg
vehicle.mass_properties.cargo = 1000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 358.25
vehicle.passengers = 100
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.83
wing.sweeps.quarter_chord = 59.5 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.
wing.span_efficiency = .8
wing.spans.projected = 25.6
wing.chords.root = 33.8
wing.total_length = 33.8
wing.chords.tip = 1.1
wing.chords.mean_aerodynamic = 18.4
wing.areas.reference = 358.25
wing.areas.wetted = 653. - 12.*2.4*2 # 2.4 is engine area on one side
wing.areas.exposed = 326.5
wing.areas.affected = .6*wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [14,0,-.8]
wing.aerodynamic_center = [35,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.vortex_lift = True
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
wing_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
wing_airfoil.coordinate_file = 'NACA65-203.dat'
wing.append_airfoil(wing_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 33.8/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 67. * Units.deg
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 1./source_ratio
segment.vsp_mesh.outer_radius = 1./source_ratio
segment.vsp_mesh.inner_length = .044/source_ratio
segment.vsp_mesh.outer_length = .044/source_ratio
segment.vsp_mesh.matching_TE = False
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set mid section start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 6.15/(25.6/2) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 13.8/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 48. * Units.deg
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 1./source_ratio
segment.vsp_mesh.outer_radius = .88/source_ratio
segment.vsp_mesh.inner_length = .044/source_ratio
segment.vsp_mesh.outer_length = .044/source_ratio
segment.vsp_mesh.matching_TE = False
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set tip section start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_3'
segment.percent_span_location = 5.95/(25.6/2) + wing.Segments['section_2'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 4.4/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 71. * Units.deg
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = .88/source_ratio
segment.vsp_mesh.outer_radius = .22/source_ratio
segment.vsp_mesh.inner_length = .044/source_ratio
segment.vsp_mesh.outer_length = .011/source_ratio
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 0.74 #
wing.sweeps.quarter_chord = 60 * Units.deg
wing.thickness_to_chord = 0.04
wing.taper = 0.14
wing.span_efficiency = 0.9
wing.spans.projected = 6.0 #
wing.chords.root = 14.5
wing.total_length = 14.5
wing.chords.tip = 2.7
wing.chords.mean_aerodynamic = 8.66
wing.areas.reference = 33.91 #
wing.areas.wetted = 76.
wing.areas.exposed = 38.
wing.areas.affected = 33.91
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [42.,0,1.]
wing.aerodynamic_center = [50,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
tail_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
tail_airfoil.coordinate_file = 'supertail_refined.dat'
wing.append_airfoil(tail_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 14.5/14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 63. * Units.deg
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 2.9/source_ratio
segment.vsp_mesh.outer_radius = 1.5/source_ratio
segment.vsp_mesh.inner_length = .044/source_ratio
segment.vsp_mesh.outer_length = .044/source_ratio
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# set mid section start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 2.4/(6.0) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 7.5/14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 40. * Units.deg
segment.vsp_mesh = Data()
segment.vsp_mesh.inner_radius = 1.5/source_ratio
segment.vsp_mesh.outer_radius = .54/source_ratio
segment.vsp_mesh.inner_length = .044/source_ratio
segment.vsp_mesh.outer_length = .027/source_ratio
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 4
fuselage.seat_pitch = 1
fuselage.fineness.nose = 4.3
fuselage.fineness.tail = 6.4
fuselage.lengths.total = 61.66
fuselage.width = 2.88
fuselage.heights.maximum = 3.32 #
fuselage.heights.maximum = 3.32 #
fuselage.heights.at_quarter_length = 3.32 #
fuselage.heights.at_wing_root_quarter_chord = 3.32 #
fuselage.heights.at_three_quarters_length = 3.32 #
fuselage.areas.wetted = 447.
fuselage.areas.front_projected = 11.9
fuselage.effective_diameter = 3.1
fuselage.differential_pressure = 7.4e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
# instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 4.0
turbojet.engine_length = 12.0
turbojet.nacelle_diameter = 1.3
turbojet.inlet_diameter = 1.1
turbojet.areas = Data()
turbojet.areas.wetted = 12.5*4.7*2. # 4.7 is outer perimeter on one side
turbojet.origin = [[37.,6.,-1.3],[37.,5.3,-1.3],[37.,-5.3,-1.3],[37.,-6.,-1.3]]
# working fluid
turbojet.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
turbojet.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 = 1.0
# add to network
turbojet.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 = 3.1
# add to network
turbojet.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 = 5.0
# add to network
turbojet.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
turbojet.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
turbojet.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 = 1.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Divergening Nozzle
# ------------------------------------------------------------------
#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 = 4*140000. * Units.N #Newtons
# Note: Sizing builds the propulsor. It does not actually set the size of the turbojet
#design sizing conditions
altitude = 0.0*Units.ft
mach_number = 0.01
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'AS2'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 185000. # kg
vehicle.mass_properties.operating_empty = 78700. # kg
vehicle.mass_properties.takeoff = 185000. # kg
vehicle.mass_properties.cargo = 1000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 358.25
vehicle.passengers = 100
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.83
wing.sweep = 55 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.
wing.span_efficiency = 0.74
wing.spans.projected = 25.6
wing.chords.root = 27.66
wing.total_length = 27.66
wing.chords.tip = 0.0
wing.chords.mean_aerodynamic = 18.4
wing.areas.reference = 358.25
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [15,0,0]
wing.aerodynamic_center = [35,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.vortex_lift = True
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 0.74 #
wing.sweep = 60 * Units.deg
wing.thickness_to_chord = 0.04
wing.taper = 0.14
wing.span_efficiency = 0.9
wing.spans.projected = 5.0 #
wing.chords.root = 12.58
wing.total_length = 12.58
wing.chords.tip = 2.5
wing.chords.mean_aerodynamic = 8.66
wing.areas.reference = 33.91 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [42,0,0]
wing.aerodynamic_center = [50,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
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 = 1
fuselage.lengths.total = 61.66
fuselage.width = 2.88
fuselage.heights.maximum = 3.32 #
fuselage.areas.wetted = 523.
fuselage.areas.front_projected = 7.55
fuselage.effective_diameter = 3.1
fuselage.differential_pressure = 7.4e4 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 4.0
turbojet.engine_length = 12.5
turbojet.nacelle_diameter = 1.60
# working fluid
turbojet.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
turbojet.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 = 1.0
# add to network
turbojet.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 = 3.1
# add to network
turbojet.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 = 5.0
# add to network
turbojet.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
turbojet.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
turbojet.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 = 1.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 0.95
nozzle.pressure_ratio = 0.99
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Divergening Nozzle
# ------------------------------------------------------------------
#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 = 4*140000. * Units.N #Newtons
# Note: Sizing builds the propulsor. It does not actually set the size of the turbojet
#design sizing conditions
altitude = 0.0*Units.ft
mach_number = 0.01
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'AS2'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 52163. # kg
vehicle.mass_properties.operating_empty = 22500. # kg
vehicle.mass_properties.takeoff = 52163. # kg
vehicle.mass_properties.cargo = 1000. * Units.kilogram
vehicle.mass_properties.center_of_gravity = [26.3 * Units.feet, 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 = 125.4
vehicle.passengers = 8
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 3.63
wing.sweep = 0 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.7
wing.span_efficiency = 0.74
wing.spans.projected = 21.0
wing.chords.root = 12.9
wing.chords.tip = 1.0
wing.chords.mean_aerodynamic = 7.0
wing.areas.reference = 125.4
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.origin = [20,0,0]
wing.aerodynamic_center = [5,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 2.0 #
wing.sweep = 0 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.5
wing.span_efficiency = 0.74
wing.spans.projected = 7.0 #
wing.chords.root = 4.0
wing.chords.tip = 2.0
wing.chords.mean_aerodynamic = 3.3
wing.areas.reference = 24.5 #
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 3.0 * Units.degrees
wing.origin = [46,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 1.3 #
wing.sweep = 45 * Units.deg
wing.thickness_to_chord = 0.08
wing.taper = 0.5
wing.span_efficiency = 0.9
wing.spans.projected = 3.5 #
wing.chords.root = 6.0
wing.chords.tip = 3.0
wing.chords.mean_aerodynamic = 4.0
wing.areas.reference = 33.9 #
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [40,0,0]
wing.aerodynamic_center = [2,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
wing.transition_x_upper = 0.9
wing.transition_x_lower = 0.9
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 = 2
fuselage.seat_pitch = 1
fuselage.fineness.nose = 4.0 # These finenesses are smaller than the real value due to limitations of existing functions
fuselage.fineness.tail = 4.0
fuselage.lengths.nose = 12.
fuselage.lengths.tail = 25.5
fuselage.lengths.cabin = 11.5
fuselage.lengths.total = 49.
fuselage.lengths.fore_space = 16.3
fuselage.lengths.aft_space = 16.3
fuselage.width = 2.35
fuselage.heights.maximum = 2.55 #
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 = 4.* 59.8 # Not correct
fuselage.areas.wetted = 615.
fuselage.areas.front_projected = 5.1
fuselage.effective_diameter = 2.4
fuselage.differential_pressure = 50**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
#instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 3.0
turbojet.engine_length = 8.0
turbojet.nacelle_diameter = 1.580
# working fluid
turbojet.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
turbojet.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
turbojet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 1.0
compressor.pressure_ratio = 5.0
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 1.0
compressor.pressure_ratio = 10.0
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 5 - Low Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='low_pressure_turbine'
# setup
turbine.mechanical_efficiency = 1.0
turbine.polytropic_efficiency = 1.0
# add to network
turbojet.append(turbine)
# ------------------------------------------------------------------
# Component 6 - High Pressure Turbine
# instantiate
turbine = SUAVE.Components.Energy.Converters.Turbine()
turbine.tag='high_pressure_turbine'
# setup
turbine.mechanical_efficiency = 1.0
turbine.polytropic_efficiency = 1.0
# add to network
turbojet.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 = 1500.
combustor.pressure_ratio = 1.0
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
#nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.polytropic_efficiency = 1.0
nozzle.pressure_ratio = 1.0
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
# Component 9 - Divergening Nozzle
# ------------------------------------------------------------------
#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*15000. * Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 2.02
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Concorde'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 185000. # kg
vehicle.mass_properties.operating_empty = 78700. # kg
vehicle.mass_properties.takeoff = 183000. # kg, adjusted due to significant fuel burn on runway
vehicle.mass_properties.cargo = 1000. * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 3.75
vehicle.envelope.limit_load = 2.5
# basic parameters
vehicle.reference_area = 358.25
vehicle.passengers = 100
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "long range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.83
wing.sweeps.quarter_chord = 59.5 * Units.deg
wing.sweeps.leading_edge = 66.5 * Units.deg
wing.thickness_to_chord = 0.03
wing.taper = 0.
wing.span_efficiency = 0.9
wing.spans.projected = 25.6
wing.chords.root = 33.8
wing.total_length = 33.8
wing.chords.tip = 1.1
wing.chords.mean_aerodynamic = 18.4
wing.areas.reference = 358.25
wing.areas.wetted = 653. - 12.*2.4*2 # 2.4 is engine area on one side
wing.areas.exposed = 326.5
wing.areas.affected = .6*wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [14,0,-.8]
wing.aerodynamic_center = [35,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.vortex_lift = True
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
wing_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
# This airfoil is not a true Concorde airfoil
wing_airfoil.coordinate_file = '../Vehicles/NACA65-203.dat'
wing.append_airfoil(wing_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 33.8/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 67. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set section 2 start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 6.15/(25.6/2) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 13.8/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 48. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set section 3 start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_3'
segment.percent_span_location = 5.95/(25.6/2) + wing.Segments['section_2'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 4.4/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 71. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# set tip
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 1.1/33.8
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.03
segment.append_airfoil(wing_airfoil)
wing.Segments.append(segment)
# CG locations are approximate
# Masses from http://www.concordesst.com/fuelsys.html
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_9'
fuel_tank.mass_properties.center_of_gravity = np.array([26.5,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 11096
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_10'
fuel_tank.mass_properties.center_of_gravity = np.array([28.7,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 11943
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_1_and_4'
fuel_tank.mass_properties.center_of_gravity = np.array([31.0,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 4198+4198
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_5_and_8'
fuel_tank.mass_properties.center_of_gravity = np.array([32.9,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 7200+12838
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_6_and_7'
fuel_tank.mass_properties.center_of_gravity = np.array([37.4,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 11587+7405
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_5A_and_7A'
fuel_tank.mass_properties.center_of_gravity = np.array([40.2,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 2225+2225
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_2_and_3'
fuel_tank.mass_properties.center_of_gravity = np.array([40.2,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 4570+4570
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
wing.Fuel_Tanks.append(fuel_tank)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 0.74 #
wing.sweeps.quarter_chord = 60 * Units.deg
wing.thickness_to_chord = 0.04
wing.taper = 0.14
wing.span_efficiency = 0.9
wing.spans.projected = 6.0 #
wing.chords.root = 14.5
wing.total_length = 14.5
wing.chords.tip = 2.7
wing.chords.mean_aerodynamic = 8.66
wing.areas.reference = 33.91 #
wing.areas.wetted = 76.
wing.areas.exposed = 38.
wing.areas.affected = 33.91
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [42.,0,1.]
wing.aerodynamic_center = [50,0,0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.high_mach = True
wing.dynamic_pressure_ratio = 1.0
tail_airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
# This airfoil is not a true Concorde airfoil
tail_airfoil.coordinate_file = '../Vehicles/supersonic_tail.dat'
wing.append_airfoil(tail_airfoil)
# set root sweep with inner section
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_1'
segment.percent_span_location = 0.0
segment.twist = 0. * Units.deg
segment.root_chord_percent = 14.5/14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 63. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# set mid section start point
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_2'
segment.percent_span_location = 2.4/(6.0) + wing.Segments['section_1'].percent_span_location
segment.twist = 0. * Units.deg
segment.root_chord_percent = 7.5/14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 40. * Units.deg
segment.thickness_to_chord = 0.03
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# set tip
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.deg
segment.root_chord_percent = 2.7/14.5
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.03
segment.append_airfoil(tail_airfoil)
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 4
fuselage.seat_pitch = 1
fuselage.fineness.nose = 4.3
fuselage.fineness.tail = 6.4
fuselage.lengths.total = 61.66
fuselage.width = 2.88
fuselage.heights.maximum = 3.32 #
fuselage.heights.maximum = 3.32 #
fuselage.heights.at_quarter_length = 3.32 #
fuselage.heights.at_wing_root_quarter_chord = 3.32 #
fuselage.heights.at_three_quarters_length = 3.32 #
fuselage.areas.wetted = 447.
fuselage.areas.front_projected = 11.9
fuselage.effective_diameter = 3.1
fuselage.differential_pressure = 7.4e4 * Units.pascal # Maximum differential pressure
fuselage.OpenVSP_values = Data() # VSP uses degrees directly
fuselage.OpenVSP_values.nose = Data()
fuselage.OpenVSP_values.nose.top = Data()
fuselage.OpenVSP_values.nose.side = Data()
fuselage.OpenVSP_values.nose.top.angle = 20.0
fuselage.OpenVSP_values.nose.top.strength = 0.75
fuselage.OpenVSP_values.nose.side.angle = 20.0
fuselage.OpenVSP_values.nose.side.strength = 0.75
fuselage.OpenVSP_values.nose.TB_Sym = True
fuselage.OpenVSP_values.nose.z_pos = -.01
fuselage.OpenVSP_values.tail = Data()
fuselage.OpenVSP_values.tail.top = Data()
fuselage.OpenVSP_values.tail.side = Data()
fuselage.OpenVSP_values.tail.bottom = Data()
fuselage.OpenVSP_values.tail.top.angle = 0.0
fuselage.OpenVSP_values.tail.top.strength = 0.0
# CG locations are approximate
# Masses from http://www.concordesst.com/fuelsys.html
fuel_tank = SUAVE.Components.Energy.Storages.Fuel_Tanks.Fuel_Tank()
fuel_tank.tag = 'tank_11'
fuel_tank.mass_properties.center_of_gravity = np.array([49.8,0,0])
fuel_tank.mass_properties.fuel_mass_when_full = 10415
fuel_tank.fuel_type = SUAVE.Attributes.Propellants.Jet_A()
fuselage.Fuel_Tanks.append(fuel_tank)
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbojet Network
# ------------------------------------------------------------------
# instantiate the gas turbine network
turbojet = SUAVE.Components.Energy.Networks.Turbojet_Super()
turbojet.tag = 'turbojet'
# setup
turbojet.number_of_engines = 4.0
turbojet.engine_length = 12.0
turbojet.nacelle_diameter = 1.3
turbojet.inlet_diameter = 1.1
turbojet.areas = Data()
turbojet.areas.wetted = 12.5*4.7*2. # 4.7 is outer perimeter on one side
turbojet.origin = [[37.,6.,-1.3],[37.,5.3,-1.3],[37.,-5.3,-1.3],[37.,-6.,-1.3]]
# working fluid
turbojet.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
turbojet.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
inlet_nozzle.pressure_recovery = 0.94
# add to network
turbojet.append(inlet_nozzle)
# ------------------------------------------------------------------
# Component 3 - Low Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'low_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.88
compressor.pressure_ratio = 3.1
# add to network
turbojet.append(compressor)
# ------------------------------------------------------------------
# Component 4 - High Pressure Compressor
# instantiate
compressor = SUAVE.Components.Energy.Converters.Compressor()
compressor.tag = 'high_pressure_compressor'
# setup
compressor.polytropic_efficiency = 0.88
compressor.pressure_ratio = 5.0
# add to network
turbojet.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 = 0.89
# add to network
turbojet.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 = 0.87
# add to network
turbojet.append(turbine)
# ------------------------------------------------------------------
# Component 7 - Combustor
# instantiate
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'combustor'
# setup
combustor.efficiency = 0.94
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1440.
combustor.pressure_ratio = 0.92
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(combustor)
# ------------------------------------------------------------------
# Afterburner
# instantiate
afterburner = SUAVE.Components.Energy.Converters.Combustor()
afterburner.tag = 'afterburner'
# setup
afterburner.efficiency = 0.9
afterburner.alphac = 1.0
afterburner.turbine_inlet_temperature = 1500
afterburner.pressure_ratio = 1.0
afterburner.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
# add to network
turbojet.append(afterburner)
# ------------------------------------------------------------------
# Component 8 - Core Nozzle
# instantiate
nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()
nozzle.tag = 'core_nozzle'
# setup
nozzle.pressure_recovery = 0.95
nozzle.pressure_ratio = 1.
# add to network
turbojet.append(nozzle)
# ------------------------------------------------------------------
#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 = 40000. * Units.lbf
# Note: Sizing builds the propulsor. It does not actually set the size of the turbojet
#design sizing conditions
altitude = 60000.0*Units.ft
mach_number = 2.02
isa_deviation = 0.
# add to network
turbojet.thrust = thrust
#size the turbojet
turbojet_sizing(turbojet,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(turbojet)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle