Abrupt and gradual stalls were made in Mach ranges of 0.21-0.63 and 0.41-0.65 respectively. Abrupt pull-ups were made through Mach range of 0.21- 0.30. Mach number greatly affected maximum lift coefficient and buffeting boundary line. Buffeting boundary was defined by maximum lift coefficient only up to M = 0.64. Above M = 0.12, calculations lost their agreement with flight data. Gradual stalls showed same effect of Mach number as abrupt stalls.
Effect of Mach Number on the Maximum Lift and Buffeting Boundary Determined in Flight on a North American P-51D Airplane
1947
28 pages
Report
Keine Angabe
Englisch
Aerodynamics , Aircraft , Buffeting , Boundary layer , Flight , Aerodynamic lift , Inflight , Mach number , Stalling , Coefficients , Ati-7343 , Ati collection