The closest you'll find to such information is some work based on flap angle deflections for a few airfoils.

As for using this information to calculate how strong a wing joint or spar or wing torsional stiffness needs to be you're REALLY barking up the wrong tree. The loads you need to be dealing with are the span loading from the aircraft weight and expected G loading in turns and pulling out of dives and the wing's torsional stiffness for dealing with the pitching moments produced both by the wing airfoils camber induced pitching moments and changes in that pitching moment produced by the camber changes that come with control surface deflections. But generally by the time you make a wing strong enough span wise to carry the loading and stiff enough not to twist in torsion the control surface effects are again minor and "lost in the noise" of all the rest.

I take it from all this that you're new to model designing and this is another one of those school projects. If so you're right to consider all these aspects but you're assigning too much value to their effect. Your primary needs for the wing are to produce a wing that will carry the expected loading at the maximum G rating and that will be torsionaly stiff enough and place the spars in the correct locations to produce a wing that does not twist while flexing under that maximum loading. If you do that the wing and joints will soak up any other loading that any control surface can possibly generate with ease.