''' Boeing 737-800.py Created: Jan 2026, M Clarke ''' # ---------------------------------------------------------------------- # Imports # ---------------------------------------------------------------------- # RCAIDE imports import RCAIDE from RCAIDE.Framework.Core import Units from RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan import design_turbofan from RCAIDE.Library.Plots import * from RCAIDE.Library.Methods.Performance import * # python imports import numpy as np import matplotlib.cm as cm from copy import deepcopy import matplotlib.pyplot as plt import os import sys # ---------------------------------------------------------------------- # Main # ---------------------------------------------------------------------- def main(): # Step 1: design a vehicle vehicle = vehicle_setup() # Step 2: create aircraft configuration based on vehicle configs = configs_setup(vehicle) # Step 3: set up analysis analyses = analyses_setup(configs) # Step 4: set up a flight mission mission = mission_setup(analyses) missions = missions_setup(mission) # Step 5: execute flight profile results = missions.base_mission.evaluate() # Step 6: plot results plot_mission(results) return def vehicle_setup(): # ------------------------------------------------------------------ # File Paths # ------------------------------------------------------------------ ospath = os.path.abspath(__file__) separator = os.path.sep local_path = os.path.dirname(ospath) + separator + '..' airfoil_file_path = local_path + separator + 'Airfoils_and_Polars' + separator polar_file_path = local_path + separator + 'Airfoils_and_Polars' + separator + 'Polars' + separator # ------------------------------------------------------------------ # Initialize the Vehicle # ------------------------------------------------------------------ vehicle = RCAIDE.Vehicle() vehicle.tag = 'Boeing_737-800' # ################################################# Vehicle-level Properties ################################################# vehicle.mass_properties.max_takeoff = 79000 * Units.kilogram vehicle.mass_properties.takeoff = 79000 * Units.kilogram vehicle.mass_properties.max_fuel = 70000 * Units.lbs vehicle.mass_properties.operating_empty = 41412.0 * Units.lbs vehicle.mass_properties.max_payload = 21000. * Units.kilogram vehicle.mass_properties.payload = 0.5*vehicle.mass_properties.max_payload vehicle.mass_properties.fuel = 0.5*vehicle.mass_properties.max_fuel vehicle.mass_properties.max_zero_fuel = 62732 * Units.kilogram vehicle.mass_properties.center_of_gravity = [[21.0,0, 0]] vehicle.flight_envelope.ultimate_load = 3.75 vehicle.flight_envelope.positive_limit_load = 2.5 vehicle.flight_envelope.design_mach_number = 0.78 vehicle.flight_envelope.design_cruise_altitude = 35000*Units.feet vehicle.flight_envelope.design_range = 3500 * Units.nmi vehicle.reference_area = 124.862 * Units['meters**2'] vehicle.number_of_passengers = 166 vehicle.systems.control = "fully powered" vehicle.systems.accessories = "medium range" # ################################################# Landing Gear ############################################################# # ------------------------------------------------------------------ # Landing Gear # ------------------------------------------------------------------ main_gear = RCAIDE.Library.Components.Landing_Gear.Main_Landing_Gear() main_gear.tire_diameter = 44.5 * Units.inches main_gear.rim_diameter = 21 * Units.inches main_gear.tire_width = 16.5 * Units.inches main_gear.strut_length = 1.8 * Units.m main_gear.origin = [[18,0, -2]] main_gear.wheels = 4 main_gear.number_of_gear_types_in_tandem = 1 main_gear.number_of_wheels_in_gear_type = 2 main_gear.xz_plane_symmetric = True vehicle.append_component(main_gear) nose_gear = RCAIDE.Library.Components.Landing_Gear.Nose_Landing_Gear() nose_gear.tire_diameter = 27 * Units.inches nose_gear.rim_diameter = 15 * Units.inches nose_gear.tire_width = 7.75 * Units.inches nose_gear.strut_length = 1.8 * Units.m nose_gear.origin = [[5,0, -2]] nose_gear.wheels = 2 nose_gear.number_of_gear_types_in_tandem = 1 nose_gear.number_of_wheels_in_gear_type = 2 vehicle.append_component(nose_gear) # ################################################# Wings ##################################################################### # ------------------------------------------------------------------ # Carbo Bays # ------------------------------------------------------------------ forward_cargo_bay = RCAIDE.Library.Components.Cargo_Bays.Cargo_Bay() forward_cargo_bay.mass_properties.mass = 1850 forward_cargo_bay.origin = [[5.82, 0, -0.6]] forward_cargo_bay.length = 7.82 forward_cargo_bay.width = 2.5 forward_cargo_bay.height = 1.12 vehicle.append_component(forward_cargo_bay) aft_cargo_bay = RCAIDE.Library.Components.Cargo_Bays.Cargo_Bay() aft_cargo_bay.mass_properties.mass = 1440 aft_cargo_bay.origin = [[23.43, 0, -0.6]] aft_cargo_bay.length = 5.5 aft_cargo_bay.width = 2.5 aft_cargo_bay.height = 1.12 vehicle.append_component(aft_cargo_bay) # ################################################# Wings ##################################################################### # ------------------------------------------------------------------ # Main Wing # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Main_Wing() wing.tag = 'main_wing' wing.aspect_ratio = 10.18 wing.sweeps.quarter_chord = 25 * Units.deg wing.thickness_to_chord = 0.1 wing.taper = 0.1 wing.spans.projected = 35.8 wing.chords.root = 7.25 * Units.meter wing.chords.tip = 0.782 * Units.meter wing.chords.mean_aerodynamic = 4.235 * Units.meter wing.areas.reference = 124.862 wing.areas.wetted = 225.08 wing.origin = [[13.61,0,-0.5]] wing.aerodynamic_center = [0,0,0] wing.vertical = False wing.xz_plane_symmetric = True wing.twists.root = 2.5 * Units.degrees wing.twists.tip = 3.5 * Units.degrees # Wing Segments root_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() root_airfoil.coordinate_file = airfoil_file_path +'transonic_wing_root_section_airfoil.txt' segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'Root' segment.percent_span_location = 0.0 segment.root_chord_percent = 1. segment.dihedral_outboard = 3.5 * Units.degrees segment.twist = 2.5 * Units.degrees segment.sweeps.quarter_chord = 28.225 * Units.degrees segment.append_airfoil(root_airfoil) wing.append_segment(segment) yehudi_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() yehudi_airfoil.coordinate_file = airfoil_file_path +'transonic_wing_inboard_section_airfoil.txt' segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'Yehudi' segment.percent_span_location = 0.324 segment.root_chord_percent = 0.5 segment.twist = 2.5 * Units.degrees segment.dihedral_outboard = 5.5 * Units.degrees segment.sweeps.quarter_chord = 25. * Units.degrees segment.append_airfoil(yehudi_airfoil) wing.append_segment(segment) mid_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() mid_airfoil.coordinate_file = airfoil_file_path +'transonic_wing_outboard_section_airfoil.txt' segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'Section_2' segment.percent_span_location = 0.963 segment.root_chord_percent = 0.220 segment.dihedral_outboard = 5.5 * Units.degrees segment.sweeps.quarter_chord = 56.75 * Units.degrees segment.twist = 0 * Units.degrees segment.append_airfoil(mid_airfoil) wing.append_segment(segment) tip_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() tip_airfoil.coordinate_file = airfoil_file_path +'transonic_wing_tip_section_airfoil.txt' segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'Tip' segment.percent_span_location = 1. segment.root_chord_percent = 0.10077 segment.dihedral_outboard = 0. segment.twist = 0 * Units.degrees segment.sweeps.quarter_chord = 56.75 * Units.degrees segment.append_airfoil(tip_airfoil) wing.append_segment(segment) # control surfaces ------------------------------------------- slat = RCAIDE.Library.Components.Wings.Control_Surfaces.Slat() slat.tag = 'slat' slat.span_fraction_start = 0.2 slat.span_fraction_end = 0.963 slat.deflection = 0.0 * Units.degrees slat.chord_fraction = 0.075 wing.append_control_surface(slat) flap = RCAIDE.Library.Components.Wings.Control_Surfaces.Flap() flap.tag = 'flap' flap.span_fraction_start = 0.2 flap.span_fraction_end = 0.7 flap.deflection = 0.0 * Units.degrees flap.configuration_type = 'double_slotted' flap.chord_fraction = 0.30 wing.append_control_surface(flap) aileron = RCAIDE.Library.Components.Wings.Control_Surfaces.Aileron() aileron.tag = 'aileron' aileron.span_fraction_start = 0.7 aileron.span_fraction_end = 0.963 aileron.deflection = 0.0 * Units.degrees aileron.chord_fraction = 0.16 wing.append_control_surface(aileron) spoiler = RCAIDE.Library.Components.Wings.Control_Surfaces.Spoiler() spoiler.tag = 'spoiler' spoiler.span_fraction_start = 0.3 spoiler.span_fraction_end = 0.7 spoiler.deflection = 0.0 * Units.degrees spoiler.chord_fraction = 0.05 wing.append_control_surface(spoiler) # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Horizontal Stabilizer # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Horizontal_Tail() wing.tag = 'horizontal_stabilizer' wing.aspect_ratio = 4.99 wing.sweeps.quarter_chord = 28.2250 * Units.deg wing.thickness_to_chord = 0.08 wing.taper = 0.3333 wing.spans.projected = 14.35 wing.chords.root = 4.1 wing.chords.tip = 1.4243 wing.chords.mean_aerodynamic = 8.0 wing.areas.reference = 41.49 wing.areas.exposed = 59.354 wing.areas.wetted = 71.81 wing.twists.root = 0.0 * Units.degrees wing.twists.tip = 0.0 * Units.degrees wing.origin = [[33.02,0,1.466]] wing.aerodynamic_center = [0,0,0] wing.vertical = False wing.xz_plane_symmetric = True # Wing Segments segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'root_segment' segment.percent_span_location = 0.0 segment.twist = 0. * Units.deg segment.root_chord_percent = 1.0 segment.dihedral_outboard = 8.63 * Units.degrees segment.sweeps.quarter_chord = 28.2250 * Units.degrees segment.thickness_to_chord = .14 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tip_segment' segment.percent_span_location = 1. segment.twist = 0. * Units.deg segment.root_chord_percent = 0.3333 segment.dihedral_outboard = 0 * Units.degrees segment.sweeps.quarter_chord = 0 * Units.degrees segment.thickness_to_chord = .14 wing.append_segment(segment) # control surfaces ------------------------------------------- elevator = RCAIDE.Library.Components.Wings.Control_Surfaces.Elevator() elevator.tag = 'elevator' elevator.span_fraction_start = 0.09 elevator.span_fraction_end = 0.92 elevator.deflection = 0.0 * Units.deg elevator.chord_fraction = 0.3 wing.append_control_surface(elevator) # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Vertical Stabilizer # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Vertical_Tail() wing.tag = 'vertical_stabilizer' wing.aspect_ratio = 2.00411 wing.sweeps.quarter_chord = 31.2 * Units.deg wing.thickness_to_chord = 0.08 wing.taper = 0.1183 wing.spans.projected = 6.08916 wing.total_length = wing.spans.projected wing.chords.root = 6.7216 wing.chords.tip = 1.20 wing.chords.mean_aerodynamic = 4.0 wing.areas.reference = 34.89 wing.areas.wetted = 57.25 wing.twists.root = 0.0 * Units.degrees wing.twists.tip = 0.0 * Units.degrees wing.origin = [[30.299,0,2.25]] wing.aerodynamic_center = [0,0,0] wing.vertical = True wing.xz_plane_symmetric = False wing.t_tail = False wing.dynamic_pressure_ratio = 1.0 # Wing Segments segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tail_root' segment.percent_span_location = 0.0 segment.twist = 0. * Units.deg segment.root_chord_percent = 1. segment.dihedral_outboard = 0 * Units.degrees segment.sweeps.quarter_chord = 65 * Units.degrees segment.thickness_to_chord =.15 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tail_segment_1' segment.percent_span_location = 0.15 segment.twist = 0. * Units.deg segment.root_chord_percent = 0.62 segment.dihedral_outboard = 0. * Units.degrees segment.sweeps.quarter_chord = 32.771* Units.degrees segment.thickness_to_chord = .13 wing.append_segment(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'tail_segment_2' segment.percent_span_location = 1.0 segment.twist = 0. * Units.deg segment.root_chord_percent = 0.23 segment.dihedral_outboard = 0.0 * Units.degrees segment.sweeps.quarter_chord = 0.0 segment.thickness_to_chord = .12 wing.append_segment(segment) # control surfaces ------------------------------------------- rudder = RCAIDE.Library.Components.Wings.Control_Surfaces.Rudder() rudder.tag = 'rudder' rudder.span_fraction_start = 0.09 rudder.span_fraction_end = 0.92 rudder.deflection = 0.0 * Units.deg rudder.chord_fraction = 0.3 wing.append_control_surface(rudder) # add to vehicle vehicle.append_component(wing) # ################################################# Fuselage ################################################################ fuselage = RCAIDE.Library.Components.Fuselages.Fuselage() fuselage.seats_abreast = 6 fuselage.seat_pitch = 1 * Units.meter fuselage.fineness.nose = 1.6 fuselage.fineness.tail = 2. fuselage.lengths.nose = 6.4 * Units.meter fuselage.lengths.tail = 8.0 * Units.meter fuselage.lengths.total = 38.02 * Units.meter fuselage.lengths.fore_space = 6. * Units.meter fuselage.lengths.aft_space = 5. * Units.meter fuselage.width = 3.76 * Units.meter fuselage.heights.maximum = 3.76 * Units.meter fuselage.effective_diameter = 3.76 * Units.meter fuselage.areas.side_projected = 142.1948 * Units['meters**2'] fuselage.areas.wetted = 446.718 * Units['meters**2'] fuselage.areas.front_projected = np.pi *(fuselage.effective_diameter **2) /4 fuselage.differential_pressure = 5.0e4 * Units.pascal fuselage.heights.at_quarter_length = 3.74 * Units.meter fuselage.heights.at_three_quarters_length = 3.65 * Units.meter fuselage.heights.at_wing_root_quarter_chord = 3.74 * Units.meter cabin = RCAIDE.Library.Components.Fuselages.Cabins.Cabin() cabin.origin = [[5, 0, 0]] first_class = RCAIDE.Library.Components.Fuselages.Cabins.Classes.First() first_class.number_of_seats_abrest = 4 first_class.number_of_rows = 4 first_class.galley_lavatory_percent_x_locations = [0] first_class.type_A_exit_percent_x_locations = [0.2] cabin.append_cabin_class(first_class) business_class = RCAIDE.Library.Components.Fuselages.Cabins.Classes.Business() business_class.number_of_seats_abrest = 6 business_class.number_of_rows = 3 cabin.append_cabin_class(business_class) economy_class = RCAIDE.Library.Components.Fuselages.Cabins.Classes.Economy() economy_class.number_of_seats_abrest = 6 economy_class.number_of_rows = 18 economy_class.galley_lavatory_percent_x_locations = [1] economy_class.emergency_exit_percent_x_locations = [0.1,0.15] economy_class.type_A_exit_percent_x_locations = [0.99] cabin.append_cabin_class(economy_class) fuselage.append_cabin(cabin) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_0' segment.percent_x_location = 0.0000 segment.percent_z_location = -0.00144 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_1' segment.percent_x_location = 0.00576 segment.percent_z_location = -0.00144 segment.height = 0.7500 segment.width = 0.6500 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_2' segment.percent_x_location = 0.02017 segment.percent_z_location = -0.00050 segment.height = 1.59978 segment.width = 1.20043 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_3' segment.percent_x_location = 0.03170 segment.percent_z_location = 0.00000 segment.height = 1.96435 segment.width = 1.52783 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_4' segment.percent_x_location = 0.04899 segment.percent_z_location = 0.00431 segment.height = 2.72826 segment.width = 1.96435 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_5' segment.percent_x_location = 0.07781 segment.percent_z_location = 0.00861 segment.height = 3.49217 segment.width = 2.61913 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_6' segment.percent_x_location = 0.10375 segment.percent_z_location = 0.01005 segment.height = 3.70130 segment.width = 3.05565 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_7' segment.percent_x_location = 0.16427 segment.percent_z_location = 0.01148 segment.height = 3.92870 segment.width = 3.71043 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Circle_Segment() segment.tag = 'segment_8' segment.percent_x_location = 0.22478 segment.percent_z_location = 0.01148 segment.height = 3.92870 segment.width = 3.92870 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Circle_Segment() segment.tag = 'segment_9' segment.percent_x_location = 0.69164 segment.percent_z_location = 0.01292 segment.height = 3.81957 segment.width = 3.81957 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Circle_Segment() segment.tag = 'segment_10' segment.percent_x_location = 0.71758 segment.percent_z_location = 0.01292 segment.height = 3.81957 segment.width = 3.81957 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_11' segment.percent_x_location = 0.78098 segment.percent_z_location = 0.01722 segment.height = 3.49217 segment.width = 3.71043 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_12' segment.percent_x_location = 0.85303 segment.percent_z_location = 0.02296 segment.height = 3.05565 segment.width = 3.16478 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_13' segment.percent_x_location = 0.91931 segment.percent_z_location = 0.03157 segment.height = 2.40087 segment.width = 1.96435 fuselage.append_segment(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_14' segment.percent_x_location = 1.00 segment.percent_z_location = 0.04593 segment.height = 1.09130 segment.width = 0.21826 fuselage.append_segment(segment) # add to vehicle vehicle.append_component(fuselage) # ################################################# Energy Network ####################################################### #------------------------------------------------------------------------------------------------------------------------- # Turbofan Network #------------------------------------------------------------------------------------------------------------------------- net = RCAIDE.Framework.Networks.Fuel() #------------------------------------------------------------------------------------------------------------------------- # Fuel Distribution Line #------------------------------------------------------------------------------------------------------------------------- fuel_line = RCAIDE.Library.Components.Powertrain.Distributors.Fuel_Line() #------------------------------------------------------------------------------------------------------------------------------------ # Propulsor: Starboard Propulsor #------------------------------------------------------------------------------------------------------------------------------------ turbofan = RCAIDE.Library.Components.Powertrain.Propulsors.Turbofan() turbofan.tag = 'starboard_propulsor' turbofan.origin = [[13.72, 4.38,-1.5]] turbofan.length = 2.71 turbofan.bypass_ratio = 5.4 turbofan.diameter = 1.5494 turbofan.design_altitude = 35000.0*Units.ft turbofan.design_mach_number = 0.78 turbofan.design_thrust = 35000.0* Units.N # fan fan = RCAIDE.Library.Components.Powertrain.Converters.Fan() fan.tag = 'fan' fan.polytropic_efficiency = 0.93 fan.pressure_ratio = 1.7 turbofan.fan = fan # working fluid turbofan.working_fluid = RCAIDE.Library.Attributes.Gases.Air() ram = RCAIDE.Library.Components.Powertrain.Converters.Ram() ram.tag = 'ram' turbofan.ram = ram # inlet nozzle inlet_nozzle = RCAIDE.Library.Components.Powertrain.Converters.Compression_Nozzle() inlet_nozzle.tag = 'inlet nozzle' inlet_nozzle.polytropic_efficiency = 0.98 inlet_nozzle.pressure_ratio = 0.98 turbofan.inlet_nozzle = inlet_nozzle # low pressure compressor low_pressure_compressor = RCAIDE.Library.Components.Powertrain.Converters.Compressor() low_pressure_compressor.tag = 'lpc' low_pressure_compressor.polytropic_efficiency = 0.91 low_pressure_compressor.pressure_ratio = 1.9 turbofan.low_pressure_compressor = low_pressure_compressor # high pressure compressor high_pressure_compressor = RCAIDE.Library.Components.Powertrain.Converters.Compressor() high_pressure_compressor.tag = 'hpc' high_pressure_compressor.polytropic_efficiency = 0.91 high_pressure_compressor.pressure_ratio = 10.0 turbofan.high_pressure_compressor = high_pressure_compressor # low pressure turbine low_pressure_turbine = RCAIDE.Library.Components.Powertrain.Converters.Turbine() low_pressure_turbine.tag ='lpt' low_pressure_turbine.mechanical_efficiency = 0.99 low_pressure_turbine.polytropic_efficiency = 0.93 turbofan.low_pressure_turbine = low_pressure_turbine # high pressure turbine high_pressure_turbine = RCAIDE.Library.Components.Powertrain.Converters.Turbine() high_pressure_turbine.tag ='hpt' high_pressure_turbine.mechanical_efficiency = 0.99 high_pressure_turbine.polytropic_efficiency = 0.93 turbofan.high_pressure_turbine = high_pressure_turbine # combustor combustor = RCAIDE.Library.Components.Powertrain.Converters.Combustor() combustor.tag = 'Comb' combustor.efficiency = 0.99 combustor.alphac = 1.0 combustor.turbine_inlet_temperature = 1600 combustor.pressure_ratio = 0.95 combustor.air_mass_flow_rate_take_off = 40 combustor.air_data = RCAIDE.Library.Attributes.Gases.Air() combustor.fuel_to_air_ratio_take_off = 0.025 # [-] combustor.fuel_data = RCAIDE.Library.Attributes.Propellants.Jet_A1() combustor.fuel_data.stoichiometric_fuel_air_ratio = 0.068 combustor.fuel_data.heat_of_vaporization = 360000 combustor.fuel_data.fuel_surrogate_S1 = {'NC12H26':0.404, 'IC8H18':0.295, 'TMBENZ' : 0.073,'NPBENZ':0.228, 'C10H8':0.02} combustor.fuel_data.temperature = 298.15 combustor.fuel_data.pressure = 101325 combustor.fuel_data.kinetic_mechanism = 'Fuel.yaml' turbofan.combustor = combustor # core nozzle core_nozzle = RCAIDE.Library.Components.Powertrain.Converters.Expansion_Nozzle() core_nozzle.tag = 'core nozzle' core_nozzle.polytropic_efficiency = 0.95 core_nozzle.pressure_ratio = 0.99 turbofan.core_nozzle = core_nozzle # fan nozzle fan_nozzle = RCAIDE.Library.Components.Powertrain.Converters.Expansion_Nozzle() fan_nozzle.tag = 'fan nozzle' fan_nozzle.polytropic_efficiency = 0.95 fan_nozzle.pressure_ratio = 0.99 turbofan.fan_nozzle = fan_nozzle # design turbofan design_turbofan(turbofan) # Nacelle nacelle = RCAIDE.Library.Components.Nacelles.Body_of_Revolution_Nacelle() nacelle.diameter = 1.6 nacelle.length = 2.71 nacelle.tag = 'starboard_nacelle' nacelle.inlet_diameter = 2.0 nacelle.origin = [[13.5,4.38,-1.5]] nacelle.areas.wetted = 1.1*np.pi*nacelle.diameter*nacelle.length nacelle_airfoil = RCAIDE.Library.Components.Airfoils.NACA_4_Series_Airfoil() nacelle_airfoil.NACA_4_Series_code = '2410' nacelle.append_airfoil(nacelle_airfoil) turbofan.nacelle = nacelle # append propulsor to network net.propulsors.append(turbofan) #------------------------------------------------------------------------------------------------------------------------------------ # Propulsor: Port Propulsor #------------------------------------------------------------------------------------------------------------------------------------ turbofan_2 = deepcopy(turbofan) turbofan_2.tag = 'port_propulsor' turbofan_2.origin = [[13.72,-4.38,-1.1]] turbofan_2.nacelle.tag = 'port_nacelle' turbofan_2.nacelle.origin = [[13.5,-4.38,-1.5]] # append propulsor to network net.propulsors.append(turbofan_2) #------------------------------------------------------------------------------------------------------------------------- # Energy Source: Fuel Tank #------------------------------------------------------------------------------------------------------------------------- inboard_tank = RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank(vehicle.wings.main_wing) inboard_tank.fuel = RCAIDE.Library.Attributes.Propellants.Jet_A() inboard_tank.segments_bounding_tank = ['root','yehudi'] fuel_line.fuel_tanks.append(inboard_tank) outboard_tank = RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Integral_Tank(vehicle.wings.main_wing) outboard_tank.fuel = RCAIDE.Library.Attributes.Propellants.Jet_A() outboard_tank.segments_bounding_tank = ['yehudi', 'section_2'] fuel_line.fuel_tanks.append(outboard_tank) #------------------------------------------------------------------------------------------------------------------------------------ # Assign propulsors to fuel line to network fuel_line.assigned_propulsors = [[turbofan.tag, turbofan_2.tag]] #------------------------------------------------------------------------------------------------------------------------------------ # Append fuel line to fuel line to network net.fuel_lines.append(fuel_line) # Append energy network to aircraft vehicle.append_energy_network(net) #------------------------------------------------------------------------------------------------------------------------- # Done ! #------------------------------------------------------------------------------------------------------------------------- return vehicle # ---------------------------------------------------------------------- # Define the Configurations # --------------------------------------------------------------------- def configs_setup(vehicle): # ------------------------------------------------------------------ # Initialize Configurations # ------------------------------------------------------------------ configs = RCAIDE.Library.Components.Configs.Config.Container() base_config = RCAIDE.Library.Components.Configs.Config(vehicle) base_config.tag = 'base' configs.append(base_config) # ------------------------------------------------------------------ # Initialize Configurations # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(vehicle) config.tag = 'idle' for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # ------------------------------------------------------------------ # Cruise Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'cruise' configs.append(config) # ------------------------------------------------------------------ # Cruise Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'descent' config.wings['main_wing'].control_surfaces.spoiler.deflection = 45. * Units.deg configs.append(config) # ------------------------------------------------------------------ # Takeoff Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'takeoff' config.wings['main_wing'].control_surfaces.flap.deflection = 20. * Units.deg config.wings['main_wing'].control_surfaces.slat.deflection = 30. * Units.deg config.networks.fuel.propulsors['starboard_propulsor'].fan.angular_velocity = 3470. * Units.rpm config.networks.fuel.propulsors['port_propulsor'].fan.angular_velocity = 3470. * Units.rpm config.networks.fuel.propulsors['starboard_propulsor'].fan.rotation = 3470. # N1 speed config.networks.fuel.propulsors['port_propulsor'].fan.rotation = 3470. # N1 speed config.networks.fuel.propulsors['starboard_propulsor'].fan_nozzle.noise_speed = 315. config.networks.fuel.propulsors['port_propulsor'].fan_nozzle.noise_speed = 315. config.networks.fuel.propulsors['starboard_propulsor'].core_nozzle.noise_speed = 415. config.networks.fuel.propulsors['port_propulsor'].core_nozzle.noise_speed = 415. for landing_gear in config.landing_gears: landing_gear.gear_extended = True config.V2_VS_ratio = 1.21 configs.append(config) # ------------------------------------------------------------------ # Cutback Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'cutback' config.wings['main_wing'].control_surfaces.flap.deflection = 20. * Units.deg config.wings['main_wing'].control_surfaces.slat.deflection = 20. * Units.deg config.networks.fuel.propulsors['starboard_propulsor'].fan.angular_velocity = 2780. * Units.rpm config.networks.fuel.propulsors['port_propulsor'].fan.angular_velocity = 2780. * Units.rpm config.networks.fuel.propulsors['starboard_propulsor'].fan.rotation = 2780. config.networks.fuel.propulsors['port_propulsor'].fan.rotation = 2780. config.networks.fuel.propulsors['starboard_propulsor'].fan_nozzle.noise_speed = 210. config.networks.fuel.propulsors['port_propulsor'].fan_nozzle.noise_speed = 210. config.networks.fuel.propulsors['starboard_propulsor'].core_nozzle.noise_speed = 360. config.networks.fuel.propulsors['port_propulsor'].core_nozzle.noise_speed = 360. for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # ------------------------------------------------------------------ # Landing Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'landing' config.wings['main_wing'].control_surfaces.flap.deflection = 30. * Units.deg config.wings['main_wing'].control_surfaces.slat.deflection = 25. * Units.deg config.networks.fuel.propulsors['starboard_propulsor'].fan.angular_velocity = 2780. * Units.rpm config.networks.fuel.propulsors['port_propulsor'].fan.angular_velocity = 2780. * Units.rpm config.networks.fuel.propulsors['starboard_propulsor'].fan.rotation = 2780. config.networks.fuel.propulsors['port_propulsor'].fan.rotation = 2780. config.networks.fuel.propulsors['starboard_propulsor'].core_nozzle.noise_speed = 92. config.networks.fuel.propulsors['port_propulsor'].core_nozzle.noise_speed = 92. config.networks.fuel.propulsors['starboard_propulsor'].fan_nozzle.noise_speed = 109.3 config.networks.fuel.propulsors['port_propulsor'].fan_nozzle.noise_speed = 109.3 for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # ------------------------------------------------------------------ # Short Field Takeoff Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'short_field_takeoff' config.wings['main_wing'].control_surfaces.flap.deflection = 20. * Units.deg config.wings['main_wing'].control_surfaces.slat.deflection = 25. * Units.deg config.networks.fuel.propulsors['starboard_propulsor'].fan.angular_velocity = 3470. * Units.rpm config.networks.fuel.propulsors['port_propulsor'].fan.angular_velocity = 3470. * Units.rpm for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # ------------------------------------------------------------------ # Short Field Takeoff Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'reverse_thrust' config.wings['main_wing'].control_surfaces.flap.deflection = 30. * Units.deg config.wings['main_wing'].control_surfaces.slat.deflection = 25. * Units.deg for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) return configs # ---------------------------------------------------------------------- # Define the Configurations # --------------------------------------------------------------------- def analyses_setup(configs): """Set up analyses for each of the different configurations.""" analyses = RCAIDE.Framework.Analyses.Analysis.Container() # Build a base analysis for each configuration. Here the base analysis is always used, but # this can be modified if desired for other cases. for tag,config in configs.items(): analysis = base_analysis(config) analyses[tag] = analysis return analyses # ---------------------------------------------------------------------- # Base Analysis # --------------------------------------------------------------------- def base_analysis(vehicle): """This is the baseline set of analyses to be used with this vehicle. Of these, the most commonly changed are the weights and aerodynamics methods.""" # ------------------------------------------------------------------ # Initialize the Analyses # ------------------------------------------------------------------ analyses = RCAIDE.Framework.Analyses.Vehicle() analyses.vehicle = vehicle # Geometry geometry = RCAIDE.Framework.Analyses.Geometry.Geometry() analyses.append(geometry) # ------------------------------------------------------------------ # Weights weights = RCAIDE.Framework.Analyses.Weights.Conventional_Transport() analyses.append(weights) # ------------------------------------------------------------------ # Aerodynamics Analysis aerodynamics = RCAIDE.Framework.Analyses.Aerodynamics.Vortex_Lattice_Method() analyses.append(aerodynamics) # ------------------------------------------------------------------ # Energy energy = RCAIDE.Framework.Analyses.Energy.Energy() analyses.append(energy) # ------------------------------------------------------------------ # Planet Analysis planet = RCAIDE.Framework.Analyses.Planets.Earth() analyses.append(planet) # ------------------------------------------------------------------ # Atmosphere Analysis atmosphere = RCAIDE.Framework.Analyses.Atmospheric.US_Standard_1976() analyses.append(atmosphere) # done! return analyses # ---------------------------------------------------------------------- # Define the Mission # ---------------------------------------------------------------------- def mission_setup(analyses): """This function defines the baseline mission that will be flown by the aircraft in order to compute performance.""" # ------------------------------------------------------------------ # Initialize the Mission # ------------------------------------------------------------------ mission = RCAIDE.Framework.Mission.Sequential_Segments() mission.tag = 'the_mission' Segments = RCAIDE.Framework.Mission.Segments base_segment = Segments.Segment() base_segment.state.numerics.solver.type = 'root_finder' # ------------------------------------------------------------------------------------------------------------------------------------ # Takeoff # ------------------------------------------------------------------------------------------------------------------------------------ segment = Segments.Ground.Takeoff(base_segment) segment.tag = "Takeoff_Ground_Run" segment.analyses.extend( analyses.takeoff ) segment.velocity_start = 0.* Units.knots segment.velocity_end = 167.0 * Units['knots'] segment.friction_coefficient = 0.03 segment.altitude = 0.0 segment.throttle = 1.0 mission.append_segment(segment) # ------------------------------------------------------------------------------------------------------------------------------------ # Takeoff Roll # ------------------------------------------------------------------------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = "Takeoff_Climb" segment.analyses.extend( analyses.takeoff ) segment.altitude_start = 0 * Units['ft'] segment.altitude_end = 35 * Units['ft'] segment.air_speed_start = 167.0 * Units['knots'] segment.air_speed_end = 175.0 * Units['knots'] segment.climb_rate = 250 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) #------------------------------------------------------------------ # First Climb Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Climb.Constant_Speed_Constant_Rate(base_segment) segment.tag = "Inital_Climb" segment.analyses.extend( analyses.cutback ) segment.altitude_start = 0 * Units['ft'] segment.altitude_end = 1000 * Units['feet'] segment.air_speed = 200.0 * Units['knots'] segment.climb_rate = 1800 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Second Climb Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Climb.Linear_Speed_Constant_Rate(base_segment) segment.tag = "Climb_to_Cruise_1" segment.analyses.extend( analyses.cutback ) segment.altitude_end = 8000 * Units['ft'] segment.air_speed_end = 300 * Units['knots'] segment.climb_rate = 1700 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) segment = Segments.Climb.Constant_Speed_Constant_Rate(base_segment) segment.tag = "Climb_to_Cruise_4" segment.analyses.extend( analyses.cruise ) segment.altitude_end = 36000 * Units['ft'] segment.air_speed = 450 * Units['knots'] segment.climb_rate = 280 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Cruise Segment: Constant Speed Constant Altitude # ------------------------------------------------------------------ segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment) segment.tag = "cruise" segment.analyses.extend( analyses.cruise ) segment.altitude = 36000 * Units['ft'] segment.air_speed = 450 * Units['knots'] segment.distance = 7370 * Units.km # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # First Descent Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Descent.Constant_Speed_Constant_Rate(base_segment) segment.tag = "descent_1" segment.analyses.extend( analyses.cruise ) segment.altitude_end = 10000 * Units.ft segment.air_speed = 350 * Units['knots'] segment.descent_rate = 1850 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Second Descent Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Descent.Constant_Speed_Constant_Rate(base_segment) segment.tag = "approach" segment.analyses.extend( analyses.landing ) segment.altitude_end = 2000 * Units.ft segment.air_speed = 200.0 * Units['knots'] segment.descent_rate = 650 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Third Descent Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Descent.Constant_Speed_Constant_Rate(base_segment) segment.tag = "final_approach" segment.analyses.extend( analyses.landing ) segment.altitude_end = 50.0 * Units.ft segment.air_speed = 150.0 * Units['knots'] segment.descent_rate = 600.0 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------ # Fourth Descent Segment: Constant Speed Constant Rate # ------------------------------------------------------------------ segment = Segments.Descent.Constant_Speed_Constant_Rate(base_segment) segment.tag = "level_off_touchdown" segment.analyses.extend( analyses.landing ) segment.altitude_end = 0 * Units.ft segment.air_speed = 150 * Units['knots'] segment.descent_rate = 300 * Units['fpm'] # define flight dynamics to model segment.flight_dynamics.force_x = True segment.flight_dynamics.force_z = True # define flight controls segment.assigned_control_variables.throttle.active = True segment.assigned_control_variables.throttle.assigned_propulsors = [['starboard_propulsor','port_propulsor']] segment.assigned_control_variables.pitch_angle.active = True mission.append_segment(segment) # ------------------------------------------------------------------------------------------------------------------------------------ # Landing Roll # ------------------------------------------------------------------------------------------------------------------------------------ segment = Segments.Ground.Landing(base_segment) segment.tag = "Landing" segment.analyses.extend( analyses.reverse_thrust ) segment.velocity_start = 160.0 * Units['knots'] segment.velocity_end = 10 * Units.knots segment.friction_coefficient = 0.4 segment.altitude = 0.0 segment.assigned_control_variables.elapsed_time.active = True segment.assigned_control_variables.elapsed_time.initial_guess_values = [[30.]] mission.append_segment(segment) # ------------------------------------------------------------------ # Mission definition complete # ------------------------------------------------------------------ return mission def missions_setup(mission): missions = RCAIDE.Framework.Mission.Missions() mission.tag = 'base_mission' missions.append(mission) return missions # ---------------------------------------------------------------------- # Plot Mission # ---------------------------------------------------------------------- def plot_mission(results): """This function plots the results of the mission analysis and saves those results to png files.""" # Plot Flight Conditions plot_flight_conditions(results) # Plot Aerodynamic Forces plot_aerodynamic_forces(results) # Plot Aerodynamic Coefficients plot_aerodynamic_coefficients(results) # Drag Components plot_drag_components(results) # Plot Altitude, sfc, vehicle weight plot_altitude_sfc_weight(results) # Plot Velocities plot_aircraft_velocities(results) return if __name__ == '__main__': main() plt.show()