I am already working on one. They want to design a straight wing (no di, no sweep) and apply a variation version of Prandtl's approach.
It would have a center control for elevator.
2 sets of trailing edge controls on each side of the straight wing. Small deflections.
The outer will be located so when it has small deflections, it would provide proverse yaw.
The inner would be located so when it has small deflections, it would provide adverse yaw.
When the aileron deflects in a turn, each yaw value(outer,inner) is different. So now we have to add each segment algebraically hoping to come up with the proper roll/yaw combination.
It is fun to explore when things don't exist.