I'll throw this one into the discussion as to whether stall AoA is speed dependent.
I know of several aircraft where the stall AOA of the wing, even at low speeds (not even in the "normal" transonic region) is significantly affected by the variation in freestream Mach number - even at speeds as low as M0.2 freestream.
The key is that the acceleration of the flow round the rather sharp leading edge of a high performance aerofoil can generate local Mach numbers well in excess of the freestream values. So what appears to be an insignificant change in the subsonic freestream value can end up being a rather significant change in the local mach number.
And, yes, this even applies to the low speed landing configuration ...