def full_setup():
# Vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# Vehicle analyses
configs_analyses = analyses_setup(configs)
# Mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
return configs, analyses
def full_setup():
# Vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# Vehicle analyses
configs_analyses = analyses_setup(configs)
# Mission analyses
mission = mission_setup(configs_analyses)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
return configs, analyses
def main():
# initialize the vehicle
vehicle = vehicle_setup()
# initalize the aero model
aerodynamics = SUAVE.Analyses.Aerodynamics.Supersonic_Zero()
aerodynamics.geometry = vehicle
aerodynamics.settings.drag_coefficient_increment = 0.0000
aerodynamics.settings.span_efficiency = 0.95
aerodynamics.settings.wave_drag_type = 'Sears-Haack'
aerodynamics.settings.volume_wave_drag_scaling = 2.3 # calibrated to Concorde results
aerodynamics.initialize()
#no of test points
test_num = 3
#specify the angle of attack
angle_of_attacks = np.linspace(-.0174, .0174 * 3,
test_num)[:, None] #* Units.deg
# Cruise conditions (except Mach number)
state = SUAVE.Analyses.Mission.Segments.Conditions.State()
state.conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
)
state.expand_rows(test_num)
# --------------------------------------------------------------------
# Initialize variables needed for CL and CD calculations
# Use a pre-run random order for values
# --------------------------------------------------------------------
Mc = np.array([[1.03], [1.5], [2.0]])
rho = np.array([[0.16], [0.16], [0.16]])
mu = np.array([[1.42e-05], [1.42e-05], [1.42e-05]])
T = np.array([[217.], [217.], [217.]])
pressure = np.array([[10000.], [10000.], [10000.]])
re = np.array([[6.0e6], [6.0e6], [6.0e6]])
air = Air()
a = air.compute_speed_of_sound(T, pressure)
re = rho * a * Mc / mu
state.conditions.freestream.mach_number = Mc
state.conditions.freestream.density = rho
state.conditions.freestream.dynamic_viscosity = mu
state.conditions.freestream.temperature = T
state.conditions.freestream.pressure = pressure
state.conditions.freestream.reynolds_number = re
state.conditions.aerodynamics.angle_of_attack = angle_of_attacks
# --------------------------------------------------------------------
# Surrogate
# --------------------------------------------------------------------
#call the aero model
results = aerodynamics.evaluate(state)
#build a polar for the markup aero
polar = Data()
CL = results.lift.total
CD = results.drag.total
polar.lift = CL
polar.drag = CD
# load older results
#save_results(polar)
old_polar = load_results()
# check the results
check_results(polar, old_polar)
return