PAINLESS,

The AoA that you end up with, and thus the elevator throw you end up with, is determined entirely by the amount of lift you need to generate for the desired turning radius. The problem I am trying to think of solutions for is the situation where you need so much AoA that profile drag goes up as a result. Think of flaperons as a way to have a variable camber wing, which is exactly what flaps are. In a perfect world, you might select an airfoil section that would give you enough lift for level flight at zero AoA. Then, select an amount of camber, or flaperon deflection, which gives the needed lift for the desired turning radius, ideally at zero AoA. You may not hit zero, but by increasing camber, the needed AoA, will be lower than if you left the main wing camber the same. In any case, the required AoA, and elevator throw, should be considerably less than without flap(eron)s. Incidently, independent flaps may end up being the better solution. I initially thought of flaperons for mechanical simplicity.

The plane will certainly slow down, but I think it's a safe assumption that you get less drag by increasing camber than by increasing AoA, especially since it reduces the fuselage AoA during the turn.

The potential problem is that a wing with deflected flaps is not as efficient as a rigid wing with the correct camber. Even so, my gut feel is that you would come out ahead. I assume that one of the common airfoil programs would be able to handle an airfoil section which represents a wing with a flap selected, so it shouldn't be too hard for someone to get a rough idea how this would work.

banktoturn