The thing to remember is that the reference frame we consider is important. We need to look at the problem from the reference frame of the aircraft to get any meaningful answers.
When this is done, and bearing in mind that yaw is lateral movement about the longitudinal axis of the aircraft, it can be seen that, in a perfectly balanced turn, any resultant yawing effect from aileron input, will, by definition of the
balanced turn, be negated by rudder input. That is, no yawing will be occurring as it has been cancelled out by pilot input.
That is my understanding.
V1R
