Comparison of Flight Test and Wind Tunnel Performance Characteristics of the X-24B Research Aircraft

Abstract : This report presents the flight-determined lift and drag characteristics of the X-24B research aircraft and compares them to wind tunnel predictions. Lift and drag data were computed from onboard measured accelerations and flight conditions while the aircraft was in gliding flight. Performance data were obtained up to a maximum Mach number of 1.72. Flight test and wind tunnel data were in general agreement, although the lift curve slope was less than predicted at most Mach numbers. The drag-due-to-lift was higher than predicted in all cases. Values of maximum lift-to-drag ratio were less than predicted for all flight conditions where comparisons could be made. The maximum subsonic lift-to-drag ratio was 4.5.