I have noticed that in tut_mission_B737, the vehicle was defined to have flaps, slats and ailerons on the main wing. In tut_mission_B737_AVL, there doesn't appear to be any addition of control surfaces to the main wing. When I tried to add control surfaces (aileron) to
tut_mission_B737_AVL, it gives me the error:
case_res.stability.alpha_derivatives.yaw_moment_derivative = float(lines[40+num_ctrl][24:34].strip()) # Cn_a
ValueError: could not convert string to float: ''
How would I add control surfaces to the wing whilst using AVL for analyses Aerodynamics and Stability?