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Embraer_190.py
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Embraer_190.py
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# Embraer_190
#
# Created: Feb 2017, M. Vegh (data taken from Embraer_E190_constThr/mission_Embraer_E190_constThr, and Regional_Jet_Optimization/Vehicles2.py), takeoff_field_length/takeoff_field_length.py, landing_field_length/landing_field_length.py
# Modified:
""" setup file for the E190 vehicle
"""
# ----------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------
import numpy as np
import SUAVE
from SUAVE.Core import Units
from SUAVE.Methods.Propulsion.turbofan_sizing import turbofan_sizing
from SUAVE.Methods.Geometry.Two_Dimensional.Planform import wing_planform
# ----------------------------------------------------------------------
# Define the Vehicle
# ----------------------------------------------------------------------
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Embraer_E190AR'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties (http://www.embraercommercialaviation.com/AircraftPDF/E190_Weights.pdf)
vehicle.mass_properties.max_takeoff = 51800. # kg
vehicle.mass_properties.operating_empty = 27837. # kg
vehicle.mass_properties.takeoff = 51800. # kg
vehicle.mass_properties.max_zero_fuel = 40900. # kg
vehicle.mass_properties.max_payload = 13063. # kg
vehicle.mass_properties.max_fuel = 12971. # kg
vehicle.mass_properties.cargo = 0.0 # kg
vehicle.mass_properties.center_of_gravity = [16.8, 0, 1.6]#[[60 * Units.feet, 0, 0]] # Not correct
vehicle.mass_properties.moments_of_inertia.tensor = [[10 ** 5, 0, 0],[0, 10 ** 6, 0,],[0,0, 10 ** 7]] # Not Correct
# envelope properties
vehicle.envelope.ultimate_load = 3.5
vehicle.envelope.limit_load = 1.5
# basic parameters
vehicle.reference_area = 92.
vehicle.passengers = 114
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = 92.0
wing.aspect_ratio = 8.4
wing.sweeps.quarter_chord = 23.0 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.28
wing.dihedral = 5.00
wing.origin = [13,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.flaps.type = 'double_slotted'
wing.flaps.chord = 0.28
wing.flaps.span_start = 0.11
wing.flaps.span_end = 0.85
wing = wing_planform(wing)
wing.areas.exposed = 0.80 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.span_efficiency = 1.0
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.areas.reference = 26.0
wing.aspect_ratio = 5.5
wing.sweeps.quarter_chord = 34.5 * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.11
wing.dihedral = 8.00
wing.origin = [32,0,0]
wing.vertical = False
wing.symmetric = True
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 2.0 * Units.degrees
wing.twists.tip = 2.0 * Units.degrees
wing.span_efficiency = 0.90
wing.dynamic_pressure_ratio = 0.90
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.areas.reference = 16.0
wing.aspect_ratio = 1.7
wing.sweeps.quarter_chord = 35. * Units.deg
wing.thickness_to_chord = 0.11
wing.taper = 0.31
wing.dihedral = 0.00
wing.origin = [32,0,0]
wing.vertical = True
wing.symmetric = False
wing.high_lift = False
wing = wing_planform(wing)
wing.areas.exposed = 0.9 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.span_efficiency = 0.90
wing.dynamic_pressure_ratio = 1.00
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.origin = [[0,0,0]]
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 4
fuselage.seat_pitch = 0.7455
fuselage.fineness.nose = 2.0
fuselage.fineness.tail = 3.0
fuselage.lengths.nose = 6.0
fuselage.lengths.tail = 9.0
fuselage.lengths.cabin = 21.24
fuselage.lengths.total = 36.24
fuselage.lengths.fore_space = 0.
fuselage.lengths.aft_space = 0.
fuselage.width = 3.18
fuselage.heights.maximum = 4.18
fuselage.heights.at_quarter_length = 3.18
fuselage.heights.at_three_quarters_length = 3.18
fuselage.heights.at_wing_root_quarter_chord = 4.00
fuselage.areas.side_projected = 239.20
fuselage.areas.wetted = 327.01
fuselage.areas.front_projected = 8.0110
fuselage.effective_diameter = 3.18
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Turbofan Network
# ------------------------------------------------------------------
#initialize the gas turbine network
gt_engine = SUAVE.Components.Energy.Networks.Turbofan()
gt_engine.tag = 'turbofan'
gt_engine.number_of_engines = 2.0
gt_engine.bypass_ratio = 5.4
gt_engine.engine_length = 2.71
gt_engine.nacelle_diameter = 2.05
#compute engine areas)
Amax = (np.pi/4.)*gt_engine.nacelle_diameter**2.
Awet = 1.1*np.pi*gt_engine.nacelle_diameter*gt_engine.engine_length # 1.1 is simple coefficient
#Assign engine areas
gt_engine.areas.wetted = Awet
#set the working fluid for the network
working_fluid = SUAVE.Attributes.Gases.Air()
#add working fluid to the network
gt_engine.working_fluid = working_fluid
#Component 1 : ram, to convert freestream static to stagnation quantities
ram = SUAVE.Components.Energy.Converters.Ram()
ram.tag = 'ram'
#add ram to the network
gt_engine.ram = ram
#Component 2 : inlet nozzle
inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
inlet_nozzle.tag = 'inlet nozzle'
inlet_nozzle.polytropic_efficiency = 0.98
inlet_nozzle.pressure_ratio = 0.98
#add inlet nozzle to the network
gt_engine.inlet_nozzle = inlet_nozzle
#Component 3 :low pressure compressor
low_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
low_pressure_compressor.tag = 'lpc'
low_pressure_compressor.polytropic_efficiency = 0.91
low_pressure_compressor.pressure_ratio = 1.9
#add low pressure compressor to the network
gt_engine.low_pressure_compressor = low_pressure_compressor
#Component 4 :high pressure compressor
high_pressure_compressor = SUAVE.Components.Energy.Converters.Compressor()
high_pressure_compressor.tag = 'hpc'
high_pressure_compressor.polytropic_efficiency = 0.91
high_pressure_compressor.pressure_ratio = 10.0
#add the high pressure compressor to the network
gt_engine.high_pressure_compressor = high_pressure_compressor
#Component 5 :low pressure turbine
low_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
low_pressure_turbine.tag='lpt'
low_pressure_turbine.mechanical_efficiency = 0.99
low_pressure_turbine.polytropic_efficiency = 0.93
#add low pressure turbine to the network
gt_engine.low_pressure_turbine = low_pressure_turbine
#Component 5 :high pressure turbine
high_pressure_turbine = SUAVE.Components.Energy.Converters.Turbine()
high_pressure_turbine.tag='hpt'
high_pressure_turbine.mechanical_efficiency = 0.99
high_pressure_turbine.polytropic_efficiency = 0.93
#add the high pressure turbine to the network
gt_engine.high_pressure_turbine = high_pressure_turbine
#Component 6 :combustor
combustor = SUAVE.Components.Energy.Converters.Combustor()
combustor.tag = 'Comb'
combustor.efficiency = 0.99
combustor.alphac = 1.0
combustor.turbine_inlet_temperature = 1500
combustor.pressure_ratio = 0.95
combustor.fuel_data = SUAVE.Attributes.Propellants.Jet_A()
#add the combustor to the network
gt_engine.combustor = combustor
#Component 7 :core nozzle
core_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
core_nozzle.tag = 'core nozzle'
core_nozzle.polytropic_efficiency = 0.95
core_nozzle.pressure_ratio = 0.99
#add the core nozzle to the network
gt_engine.core_nozzle = core_nozzle
#Component 8 :fan nozzle
fan_nozzle = SUAVE.Components.Energy.Converters.Expansion_Nozzle()
fan_nozzle.tag = 'fan nozzle'
fan_nozzle.polytropic_efficiency = 0.95
fan_nozzle.pressure_ratio = 0.99
#add the fan nozzle to the network
gt_engine.fan_nozzle = fan_nozzle
#Component 9 : fan
fan = SUAVE.Components.Energy.Converters.Fan()
fan.tag = 'fan'
fan.polytropic_efficiency = 0.93
fan.pressure_ratio = 1.7
#add the fan to the network
gt_engine.fan = fan
#Component 10 : thrust (to compute the thrust)
thrust = SUAVE.Components.Energy.Processes.Thrust()
thrust.tag ='compute_thrust'
#total design thrust (includes all the engines)
thrust.total_design = 37278.0* Units.N #Newtons
#design sizing conditions
altitude = 35000.0*Units.ft
mach_number = 0.78
isa_deviation = 0.
# add thrust to the network
gt_engine.thrust = thrust
#size the turbofan
turbofan_sizing(gt_engine,mach_number,altitude)
# add gas turbine network gt_engine to the vehicle
vehicle.append_component(gt_engine)
fuel =SUAVE.Components.Physical_Component()
vehicle.fuel =fuel
fuel.mass_properties.mass =vehicle.mass_properties.max_takeoff-vehicle.mass_properties.max_fuel
fuel.origin =vehicle.wings.main_wing.mass_properties.center_of_gravity
fuel.mass_properties.center_of_gravity=vehicle.wings.main_wing.aerodynamic_center
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
# ----------------------------------------------------------------------
# Define the Configurations
# ---------------------------------------------------------------------
def configs_setup(vehicle):
# ------------------------------------------------------------------
# Initialize Configurations
# ------------------------------------------------------------------
configs = SUAVE.Components.Configs.Config.Container()
base_config = SUAVE.Components.Configs.Config(vehicle)
base_config.tag = 'base'
configs.append(base_config)
# ------------------------------------------------------------------
# Cruise Configuration
# ------------------------------------------------------------------
config = SUAVE.Components.Configs.Config(base_config)
config.tag = 'cruise'
configs.append(config)
# ------------------------------------------------------------------
# Takeoff Configuration
# ------------------------------------------------------------------
config = SUAVE.Components.Configs.Config(base_config)
config.tag = 'takeoff'
config.wings['main_wing'].flaps.angle = 20. * Units.deg
config.wings['main_wing'].slats.angle = 25. * Units.deg
config.V2_VS_ratio = 1.21
configs.append(config)
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
config = SUAVE.Components.Configs.Config(base_config)
config.tag = 'landing'
config.wings['main_wing'].flaps.angle = 30. * Units.deg
config.wings['main_wing'].slats.angle = 25. * Units.deg
config.Vref_VS_ratio = 1.23
configs.append(config)
# ------------------------------------------------------------------
# Short Field Takeoff Configuration
# ------------------------------------------------------------------
config = SUAVE.Components.Configs.Config(base_config)
config.tag = 'short_field_takeoff'
config.wings['main_wing'].flaps.angle = 20. * Units.deg
config.wings['main_wing'].slats.angle = 25. * Units.deg
config.V2_VS_ratio = 1.21
# payload?
configs.append(config)
# done!
return configs