conditions.aerodynamics.lift_coefficient = inviscid_lift
conditions.aerodynamics.lift_breakdown = Data()
conditions.aerodynamics.lift_breakdown.compressible_wings = Data()
conditions.aerodynamics.lift_breakdown.total = inviscid_lift
conditions.aerodynamics.lift_breakdown.compressible_wings["main_wing"] = inviscid_lift // currently using vehicle drag for wing
// Inviscid drag, zeros are a placeholder for possible future implementation
After Change
state.conditions.aerodynamics.lift_breakdown.compressible_wings = inviscid_lift
// Inviscid drag, zeros are a placeholder for possible future implementation
inviscid_drag = np.zeros([data_len,1])
state.conditions.aerodynamics.inviscid_drag_coefficient = inviscid_drag
return inviscid_lift, inviscid_drag
