propulsive_efficiency=0.85,
tsfc=.00019, # Thrust Specific Fuel Consumption
energy_source_type=energy_source_type,
thrust_source_type=thrust_source_type,
stall_speed=cruise_speed * 0.6,
climb_speed=cruise_speed * 0.8,
turn_speed=cruise_speed * 0.8,
landing_distance_ft=landing_distance_ft,
wing_loading_lbf_ft2=wing_loading_lbf_ft2,
thrust_to_weight=thrust_to_weight,
ref_wing_loading_lbf_ft2=ref_wing_loading_lbf_ft2,
ref_thrust_to_weight=ref_thrust_to_weight,
)
prob = Problem()
prob.aircraft = aircraft
comp = IndepVarComp()
comp.add_output('density', val=1.225, shape=shape)
comp.add_output('payload_weight', val=payload_weight, shape=shape)
comp.add_output('crew_weight', val=crew_weight, shape=shape)
comp.add_output('range_km', val=range_km, shape=shape)
comp.add_output('lift_to_drag_ratio', val=lift_to_drag_ratio, shape=shape)
comp.add_output('oswald_efficiency', val=0.8, shape=shape)
comp.add_output('aspect_ratio', val=6.96, shape=shape)
comp.add_output('cruise_speed', val=cruise_speed, shape=shape)
comp.add_output('CD0', val=0.0350, shape=shape)
prob.model.add_subsystem('inputs_comp', comp, promotes=['*']) # Adding the subsystem of Independent Variable Components to your model.
# This will create a SizingGrossWeightGroup for your openmdao model.
group = SizingGrossWeightGroup(
