Shoe: I agree wrote it a slightly diff way. Why we are even debating compressible fluid flow questions in this forum I don't know. Fighter aircraft usually operate around 50% MAC when going to supersonic conditions because lift is generated via a different pressure differential.
Mach >1 pressure gradients on the top of the wing are fairly even while in M<1 pressure gradients are highest at leading edge. Thus the Cg moves when going through the transonic range to supersonic.

Brian