A control surface deflecting alters both the camber of the airfoil and the angle of incidence both at the same time. How that will alter the Cl would be easy if it were only an angle of attack change. But throwing in the camber change at the same time confuses the issue.

Then there's also what happens as the wing begins to accellerate into the rolling rate. The angle of attack of the wings when the control surfaces are first deflected is one thing and easy to figure out. But then this immediately begins to change as the wing begins to gain rolling velocity. What the final value of a constant roll rate would be has to be calculated based on the rolling rate and how far out from the fuselage each position of the wing is located at since the feet per revolution covered is different for the root than the tips.

All of which is to say "I don't know". I only know enough to know that it's a messy situation.... which is likely why few folks this side of Boeing and Airbus and other such places would bother.