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(