It think is fair enough for me to give more information. Basically I will use this information to optimize the internal structure of the wing. As it is I have a three section wing and the control surfaces are in the outer sections. I want to know the moments or forces that these produce so I can design a proper joint between them. Maybe obtaining the change in Cl might not be right approach but instead in finding a way of how to obtain that force and moment about my joint when the control surface deflect.

I have calculated wign lift distribution, the tail loads, and the load factors. I was thinking just to use moment equation on the wing and find my stress at the joint. However, I don't know how accurate this might be. Any suggestions is greatly appreciate it.

Thank you.