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test_AVL.py
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test_AVL.py
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# test_AVL.py
#
# Created: May 2017, M. Clarke
# Modified: Apr 2020, M. Clarke
""" setup file for a mission with a 737 using AVL
"""
# ----------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------
import SUAVE
from SUAVE.Core import Units
import numpy as np
import copy, time
from SUAVE.Core import (
Data, Container,
)
import sys
sys.path.append('../Vehicles')
# the analysis functions
from Boeing_737 import vehicle_setup, configs_setup
sys.path.append('../B737')
# the analysis functions
from mission_B737 import vehicle_setup, configs_setup, analyses_setup, mission_setup, missions_setup, simple_sizing
import copy
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
run_new_regression = False
# append AVL aerodynamic analysis
aerodynamics = SUAVE.Analyses.Aerodynamics.AVL()
aerodynamics.settings.number_spanwise_vortices = 30
aerodynamics.settings.keep_files = True
aerodynamics.geometry = copy.deepcopy(configs.cruise)
configs_analyses.cruise.append(aerodynamics)
# append AVL stability analysis
stability = SUAVE.Analyses.Stability.AVL()
stability.settings.number_spanwise_vortices = 30
stability.settings.keep_files = True
stability.geometry = copy.deepcopy(configs.cruise)
if run_new_regression:
# append AVL aerodynamic analysis
aerodynamics.settings.regression_flag = False
aerodynamics.process.compute.lift.inviscid.settings.filenames.avl_bin_name = 'CHANGE/TO/AVL/PATH'
aerodynamics.settings.save_regression_results = True
stability.settings.regression_flag = False
stability.settings.save_regression_results = True
stability.settings.filenames.avl_bin_name = 'CHANGE/TO/AVL/PATH'
else:
aerodynamics.settings.regression_flag = True
aerodynamics.settings.save_regression_results = False
aerodynamics.settings.training_file = 'cruise_aero_data.txt'
stability.settings.regression_flag = True
stability.settings.save_regression_results = False
stability.training_file = 'cruise_stability_data.txt'
configs_analyses.cruise.append(aerodynamics)
configs_analyses.cruise.append(stability)
# ------------------------------------------------------------------
# Initialize the Mission
# ------------------------------------------------------------------
mission = SUAVE.Analyses.Mission.Sequential_Segments()
mission.tag = 'the_mission'
#airport
airport = SUAVE.Attributes.Airports.Airport()
airport.altitude = 0.0 * Units.ft
airport.delta_isa = 0.0
airport.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
mission.airport = airport
# unpack Segments module
Segments = SUAVE.Analyses.Mission.Segments
# base segment
base_segment = Segments.Segment()
# ------------------------------------------------------------------
# Cruise Segment: constant speed, constant altitude
# ------------------------------------------------------------------
segment = Segments.Cruise.Constant_Speed_Constant_Altitude(base_segment)
segment.tag = "cruise"
segment.analyses.extend( configs_analyses.cruise )
segment.air_speed = 230. * Units['m/s']
segment.distance = 4000. * Units.km
segment.altitude = 10.668 * Units.km
segment.state.numerics.number_control_points = 4
# add to mission
mission.append_segment(segment)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
simple_sizing(configs, analyses)
configs.finalize()
analyses.finalize()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# lift coefficient check
lift_coefficient = results.segments.cruise.conditions.aerodynamics.lift_coefficient[0][0]
lift_coefficient_true = 0.6125259974142665
print(lift_coefficient)
diff_CL = np.abs(lift_coefficient - lift_coefficient_true)
print('CL difference')
print(diff_CL)
assert np.abs((lift_coefficient - lift_coefficient_true)/lift_coefficient_true) < 1e-6
# moment coefficient check
moment_coefficient = results.segments.cruise.conditions.stability.static.CM[0][0]
moment_coefficient_true = -0.5764667256663776
print(moment_coefficient)
diff_CM = np.abs(moment_coefficient - moment_coefficient_true)
print('CM difference')
print(diff_CM)
assert np.abs((moment_coefficient - moment_coefficient_true)/moment_coefficient_true) < 1e-6
return
if __name__ == '__main__':
main()