Originally Posted by mm43
What do you believe the Alpha Max was at 02:10:56?
Alpha Max for M=0.65, the Mach number at 02:10:56, is 7.6 degrees. The lift coefficient and AoA versus time are shown
in this graph. The lift coefficient is calculated for the normal acceleration and airspeed calculated from ground speed and vertical speed in still air, which fits the recorded airspeed prior to stall. I can't explain the strange variations of cL and AoA after 02:10:58,4 when the airplane is evidently stalled.