Not sure why I'm bothering, but anyway.
If flying in balanced straight and level flight with zero yaw and an angle of attack alpha is subjected to a pure yaw (no roll or pitch secondary effects of the yaw control) through an angle beta then the angle of attack of the wing (the whole wing, not one side or the other) will reduce by a factor proportional to cos (beta).
In a real aeroplane the resulting reduction of lift coefficient will make lift less than weight, so the aeroplane will accelerate downwards until it achieves a steady state condition where the angle of descent is equal to alpha * [1-cos(beta)].
At least I think that's it - trying to visualise it in my head because I'm posting this with my phone and don't have a whiteboard handy to sketch the diagram.
But I cannot see any situation where it would be different for the two sides of a wing with no dihederal.