Flight Test and Wind Tunnel Performance Characteristics of the X-24A lifting Body. Volume I

The objectives of determining the performance characteristics of the X-24A lifting body from flight test data and correlating these results with wind tunnel predictions were successfully accomplished. Lift and drag characteristics were computed from onboard measured accelerations and flight conditions while the vehicle was in gliding flight. Performance data were obtained over Mach number and angle of attack ranges of 0.26 to 1.5 and 1.5 to 19.6 degrees, respectively. Discrepancies were apparent between different wind tunnel predictions. However, flight test data generally exhibited lower lift and slightly lower drag than wind tunnel predictions with the result that flight test and wind tunnel L/D values were in reasonably good agreement. Effects of Mach number, vehicle control surface configuration, and landing gear deployment on performance parameters were determined. Degradation of flight performance at low subsonic Mach numbers was attributed to tip fin flow separation.