For what it's worth, way back in my college days, some of the guys on my course tied their brains in knots when the fluid dynamics lectures moved from wind tunnel mach applications (fixed, static wing) to flying applications (moving, cranked wing).
The way that my lecturer (sharp cookie) talked them round was to tell them that for a straight wing, as per the classic WW2 fighter lost in the dive scenario, the shockwave would form at the top of the wing chord and as speed build up would creep back to form a nice line just at the ailerons on the wing and likewise a smaller but deadlier one could form on the tailplane and creep back to mask the elevator, depending on the vertical arrangement of the wing and tailplane. However, he told them that the modern delta or cranked wing arrangement encouraged the shockwave to form in a line across the control surface, rather than along the entire control surface.
I can't quite recall just how accurate the explanantion is at present as it's been nigh on 20 years since I graduated, but it seemed to do the trick when I saw it used in anger.....