I guess experimental lift slope curve data is the only way to go; although I did ASSume at least part of the leftward alpha shift of those curves with increasing M would have been due to that relation, and of course in this case Mach and Reynold's numbers intertwine inseparably
...it must be a true supercritical design...I don't suppose you could provide the NACA designation for the airfoil
..would a Cm change also affect the Alpha effective?
