Does this trend of critical AoA reducing with mach number increasing continue when going supersonic?
I'm just curious because if I recall supersonic airflow can go very rapidly around rough edges (and from what I remember this is why you can use an airfoil with a diamond cross-sectional shape at supersonic speeds), though on the other hand, you have a shockwave on the leading edge that you don't have on a subsonic wing and that does tend to produce some turbulence behind it and that could make airflow separate a bit easier...