''' Title : Part 35 V-n Diagram Scope : This example computes and plots the V-n diagram for a Part-35 class aircraft Author : Matthew Clarke Date : Feb 18th, 2026 ''' # ---------------------------------------------------------------------- # Imports # ---------------------------------------------------------------------- # RCAIDE Imports import RCAIDE from RCAIDE.Framework.Core import Data,Units from RCAIDE.Library.Methods.Performance import generate_V_n_diagram from RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan import design_turbofan from RCAIDE.Library.Plots import * # python imports import os import sys import numpy as np import numpy as np import matplotlib.pyplot as plt from copy import deepcopy # ---------------------------------------------------------------------------------------------------------------------- # Part 35 V-n Diagram # ---------------------------------------------------------------------------------------------------------------------- def main(): # Set up vehicle vehicle = vehicle_setup() # Set up vehicle configs configs = configs_setup(vehicle) # create analyses analyses = analyses_setup(configs) # Vn Diagram V_n_data = generate_V_n_diagram(analyses=analyses.cruise) plot_V_n_diagram(V_n_data, vehicle) return # ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------- # ############################################################################################################################################################################ # ---------------------------------------------------------------------------------------------------------------------------------------------------------------------------- # ---------------------------------------------------------------------------------------------------------------------- # Build the Vehicle # ---------------------------------------------------------------------------------------------------------------------- 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 #------------------------------------------------------------------------------------------------------------------------------------ # ################################################# Vehicle-level Properties ######################################################## #------------------------------------------------------------------------------------------------------------------------------------ vehicle = RCAIDE.Vehicle() vehicle.tag = 'Embraer_E190AR' # mass properties (http://www.embraercommercialaviation.com/AircraftPDF/E190_Weights.pdf) vehicle.mass_properties.max_takeoff = 51800. # kg vehicle.mass_properties.takeoff = 51800. # kg vehicle.mass_properties.max_zero_fuel = 40900. # kg vehicle.mass_properties.max_fuel = 13100. # kg vehicle.mass_properties.max_payload = 12900. # kg vehicle.mass_properties.operating_empty = 27900 # vehicle.mass_properties.center_of_gravity = [[16.8, 0, 1.6]] vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # envelope properties vehicle.flight_envelope.ultimate_load = 3.5 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 = 2000 * Units.nmi vehicle.flight_envelope.category = 'normal' vehicle.flight_envelope.FAR_part_number = '25' vehicle.flight_envelope.maximum_lift_coefficient = 3 vehicle.flight_envelope.minimum_lift_coefficient = -1.5 # basic parameters vehicle.reference_area = 92. vehicle.number_of_passengers = 112 vehicle.systems.control = "fully powered" vehicle.systems.accessories = "medium range" # ------------------------------------------------------------------ # Carbo Bays # ------------------------------------------------------------------ forward_cargo_bay = RCAIDE.Library.Components.Cargo_Bays.Cargo_Bay() forward_cargo_bay.mass_properties.mass = 1850 forward_cargo_bay.origin = [[6.82, 0, -0.5]] forward_cargo_bay.length = 7.82 forward_cargo_bay.width = 1.57 forward_cargo_bay.height = 0.88 vehicle.cargo_bays.append(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, -0.5]] aft_cargo_bay.length = 5.5 aft_cargo_bay.width = 1.57 aft_cargo_bay.height = 0.88 vehicle.cargo_bays.append(aft_cargo_bay) # ################################################# 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.wheels = 4 main_gear.number_of_gear_types_in_tandem = 1 main_gear.number_of_wheels_in_gear_type = 2 main_gear.origin = [[17.96, 0, 0]] 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.wheels = 2 nose_gear.number_of_gear_types_in_tandem = 1 nose_gear.number_of_wheels_in_gear_type = 2 nose_gear.origin = [[2.49, 0, 0]] vehicle.append_component(nose_gear) #------------------------------------------------------------------------------------------------------------------------------------ # ######################################################## Wings #################################################################### #------------------------------------------------------------------------------------------------------------------------------------ # ------------------------------------------------------------------ # Main Wing # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Main_Wing() wing.tag = 'main_wing' wing.areas.reference = 92.0 wing.aspect_ratio = 8.4 wing.chords.root = 6.2 wing.chords.tip = 1.44 wing.sweeps.quarter_chord = 23.0 * Units.deg wing.thickness_to_chord = 0.1 wing.taper = 0.28 wing.dihedral = 5.00 * Units.deg wing.spans.projected = 28.72 wing.origin = [[13.3,0,-1.]] wing.vertical = False wing.xz_plane_symmetric = True wing.areas.exposed = 0.80 * wing.areas.wetted wing.twists.root = 2.0 * Units.degrees wing.twists.tip = 0.0 * Units.degrees wing.dynamic_pressure_ratio = 1.0 segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'root' segment.percent_span_location = 0.0 segment.root_chord_percent = 1. segment.thickness_to_chord = .11 segment.dihedral_outboard = 5. * Units.degrees segment.sweeps.quarter_chord = 20.6 * Units.degrees root_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() root_airfoil.coordinate_file = airfoil_file_path + 'transonic_wing_root_section_airfoil.txt' segment.append_airfoil(root_airfoil) wing.segments.append(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'yehudi' segment.percent_span_location = 0.348 segment.root_chord_percent = 0.60 segment.dihedral_outboard = 4 * Units.degrees segment.sweeps.quarter_chord = 24.1 * Units.degrees yehudi_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() yehudi_airfoil.coordinate_file = airfoil_file_path + 'transonic_wing_inboard_section_airfoil.txt' segment.append_airfoil(yehudi_airfoil) wing.segments.append(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'section_2' segment.percent_span_location = 0.961 segment.root_chord_percent = 0.25 segment.dihedral_outboard = 70. * Units.degrees segment.sweeps.quarter_chord = 40. * Units.degrees mid_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() mid_airfoil.coordinate_file = airfoil_file_path + 'transonic_wing_outboard_section_airfoil.txt' segment.append_airfoil(mid_airfoil) wing.segments.append(segment) segment = RCAIDE.Library.Components.Wings.Segments.Segment() segment.tag = 'Tip' segment.percent_span_location = 1. segment.root_chord_percent = 0.070 segment.dihedral_outboard = 0. segment.sweeps.quarter_chord = 0. tip_airfoil = RCAIDE.Library.Components.Airfoils.Airfoil() tip_airfoil.coordinate_file = airfoil_file_path + 'transonic_wing_tip_section_airfoil.txt' segment.append_airfoil(tip_airfoil) wing.segments.append(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 = 0.14 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 = 0.25 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.areas.reference = 26.0 wing.chords.root = 3.6 wing.chords.tip = 0.72 wing.aspect_ratio = 5.5 wing.spans.projected = 12 wing.sweeps.quarter_chord = 34.5 * Units.deg wing.thickness_to_chord = 0.16 wing.taper = 0.2 wing.dihedral = 8.4 * Units.degrees wing.origin = [[31,0,1.5]] wing.vertical = False wing.xz_plane_symmetric = True wing.areas.exposed = 0.9 * wing.areas.wetted wing.twists.root = 0.0 * Units.degrees wing.twists.tip = 0.0 * Units.degrees wing.dynamic_pressure_ratio = 0.90 # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Vertical Stabilizer # ------------------------------------------------------------------ wing = RCAIDE.Library.Components.Wings.Vertical_Tail() wing.tag = 'vertical_stabilizer' wing.areas.reference = 16.0 wing.aspect_ratio = 1.7 wing.spans.projected = 5.21 wing.sweeps.quarter_chord = 35. * Units.deg wing.chords.root = 4.68 wing.chords.tip = 1.45 wing.thickness_to_chord = 0.16 wing.taper = 0.31 wing.dihedral = 0.00 wing.origin = [[30.4,0,1.675]] wing.vertical = True wing.xz_plane_symmetric = False wing.areas.exposed = 0.9 * wing.areas.wetted wing.twists.root = 0.0 * Units.degrees wing.twists.tip = 0.0 * Units.degrees wing.dynamic_pressure_ratio = 1.00 # add to vehicle vehicle.append_component(wing) # ------------------------------------------------------------------ # Fuselage # ------------------------------------------------------------------ fuselage = RCAIDE.Library.Components.Fuselages.Fuselage() fuselage.origin = [[0,0,0]] fuselage.fineness.nose = 1.28 fuselage.fineness.tail = 3.48 fuselage.lengths.nose = 6.0 fuselage.lengths.tail = 9.0 fuselage.lengths.cabin = 21.24 fuselage.lengths.total = 36.24 fuselage.width = 3.01 * Units.meters fuselage.heights.maximum = 3.35 fuselage.heights.at_quarter_length = 3.35 fuselage.heights.at_three_quarters_length = 3.35 fuselage.heights.at_wing_root_quarter_chord = 3.35 fuselage.areas.side_projected = 239.20 fuselage.areas.wetted = 327.01 fuselage.areas.front_projected = np.pi * (fuselage.heights.maximum / 2) ** 2 fuselage.effective_diameter = 3.18 fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure cabin = RCAIDE.Library.Components.Fuselages.Cabins.Cabin() economy_class = RCAIDE.Library.Components.Fuselages.Cabins.Classes.Economy() economy_class.number_of_seats_abrest = 4 economy_class.number_of_rows = 28 economy_class.number_of_passengers = 106 economy_class.galley_lavatory_percent_x_locations = [0, 1] economy_class.emergency_exit_percent_x_locations = [0.5, 0.5] economy_class.type_A_exit_percent_x_locations = [0, 1] cabin.origin = [[4.65, 0, 0]] 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 segment.height = 0.0100 segment.width = 0.0100 fuselage.segments.append(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.segments.append(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.Segment() segment.tag = 'segment_2' segment.percent_x_location = 0.02017 segment.percent_z_location = 0.00000 segment.height = 1.52783 segment.width = 1.20043 fuselage.segments.append(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.segments.append(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.segments.append(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.segments.append(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.segments.append(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.segments.append(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.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.segments.append(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.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.segments.append(segment) # Segment segment = RCAIDE.Library.Components.Fuselages.Segments.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.segments.append(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.segments.append(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.segments.append(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.segments.append(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.segments.append(segment) # add to vehicle vehicle.append_component(fuselage) #------------------------------------------------------------------------------------------------------------------------------------ # Fuel Network #------------------------------------------------------------------------------------------------------------------------------------ #initialize the fuel network net = RCAIDE.Framework.Networks.Fuel() #------------------------------------------------------------------------------------------------------------------------------------ # Fuel Distribution Line #------------------------------------------------------------------------------------------------------------------------------------ fuel_line = RCAIDE.Library.Components.Powertrain.Distributors.Fuel_Line() #------------------------------------------------------------------------------------------------------------------------------------ # Fuel Tank & Fuel #------------------------------------------------------------------------------------------------------------------------------------ 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'] inboard_tank.segments_percent_chord_start = [0.15 ,0.15 ] inboard_tank.segments_percent_chord_end = [0.625 ,0.625] 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'] outboard_tank.segments_percent_chord_start = [0.15 ,0.15 ] outboard_tank.segments_percent_chord_end = [0.625,0.625] fuel_line.fuel_tanks.append(outboard_tank) fuel_tank = RCAIDE.Library.Components.Powertrain.Sources.Fuel_Tanks.Non_Integral_Tank() fuel_tank.lengths.external = 2 fuel_tank.widths.external = 2 fuel_tank.geometry_type = 'prismatic' fuel_tank.heights.external = 0.5 fuel_tank.origin = [[15.0,0.0, 0.0]] fuel_tank.fuel = RCAIDE.Library.Attributes.Propellants.Jet_A() fuel_tank.fuel.origin = [[15.0,0.0, 0.0]] fuel_line.fuel_tanks.append(fuel_tank) #------------------------------------------------------------------------------------------------------------------------------------ # Propulsor #------------------------------------------------------------------------------------------------------------------------------------ turbofan = RCAIDE.Library.Components.Powertrain.Propulsors.Turbofan() turbofan.tag = 'starboard_propulsor' turbofan.length = 145 * Units.inches turbofan.bypass_ratio = 5.4 turbofan.diameter = 53 * Units.inches turbofan.design_altitude = 35000.0*Units.ft turbofan.design_mach_number = 0.8 turbofan.design_thrust = 35000.0* Units.N#/2 turbofan.origin = [[13.15,4.38,-2.1]] turbofan.mass_properties.center_of_gravity = [[turbofan.length /2,0,0]] # Nacelle nacelle = RCAIDE.Library.Components.Nacelles.Body_of_Revolution_Nacelle() nacelle.diameter = 2.05 nacelle.length = 2.66 nacelle.tag = 'nacelle_1' nacelle.inlet_diameter = 2.0 nacelle.origin = [[12.15,4.38, -2.1]] nacelle.mass_properties.center_of_gravity = [[nacelle.length /2,0,0 ]] 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 # 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 = 1550 combustor.pressure_ratio = 0.95 combustor.fuel_data = RCAIDE.Library.Attributes.Propellants.Jet_A() 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 core_nozzle.diameter = 0.92 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 fan_nozzle.diameter = 1.659 turbofan.fan_nozzle = fan_nozzle # design turbofan design_turbofan(turbofan) # append propulsor to network net.propulsors.append(turbofan) #------------------------------------------------------------------------------------------------------------------------------------ # Port Propulsor #------------------------------------------------------------------------------------------------------------------------------------ # copy turbofan turbofan_2 = deepcopy(turbofan) turbofan_2.tag = 'port_propulsor' turbofan_2.origin = [[13.15,-4.38,-2.1]] # change origin turbofan_2.nacelle.origin = [[12.15,-4.38,-2.1]] # append propulsor to network net.propulsors.append(turbofan_2) #------------------------------------------------------------------------------------------------------------------------------------ # Assign propulsors to fuel line 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) 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) # ------------------------------------------------------------------ # Cruise Configuration # ------------------------------------------------------------------ config = RCAIDE.Library.Components.Configs.Config(base_config) config.tag = 'cruise' 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 = 25. * Units.deg for landing_gear in config.landing_gears: landing_gear.gear_extended = True 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 for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # ------------------------------------------------------------------ # Descent 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) # ------------------------------------------------------------------ # 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 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 for landing_gear in config.landing_gears: landing_gear.gear_extended = True configs.append(config) # done! return configs def analyses_setup(configs): analyses = RCAIDE.Framework.Analyses.Analysis.Container() # build a base analysis for each config for tag,config in configs.items(): analysis = base_analysis(config) analyses[tag] = analysis return analyses def base_analysis(vehicle): # ------------------------------------------------------------------ # 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 # ---------------------------------------------------------------------- # Call Main # ---------------------------------------------------------------------- if __name__ == '__main__': main() plt.show()