Originally Posted by
RR_NDB
Thanks,
RR_NDB. Good movie. So the sharp leading-edge retrofitted (as early as 1937) between the engine nacelles and the fuselage greatly reduces the wing-drop tendency in the power-on stall.
I guess that the pre-mod tendency of the stall to propagate from the wing-tips inwards in the power-on case is because the inner-wing airflow is smoothed by the propellor slipstream? But that's not to suggest that the mod results in a benign stall with power on. Is there any wash-out of the rigger's angle between root and tip? I never noticed any.
FWIW, however, here's the single paragraph describing the stall characteristics of the C-47, taken from the UK Air Ministry's Pilot's Notes for the Dakota 4, published in 1946 (my emphasis):
"There is little warning of the approach of the stall except for a slight tail buffeting which may be felt some 5 m.p.h. (kts) before the stall itself. At the stall the nose drops gently. In all cases recovery is straight-forward and easy."