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

This report discusses the flight—determined lift and drag charac— 
teriBtics 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 wag higher than predicted in all cases. Values of 
maximum lift—to—drag ratio were less than predicted for all flight condi— 
tions where comparisons could be made. The maximum subsonic lift—to— 
drag ratio was 4.5.

This report is one Of four technical report• prepared by the Air 
Force Flight Test Center (PFFTC) to provide final documentation of the 
X—24B flight test program. Referencea i, 2, 9 and 10 are related 
documents reporting on other aspects Of the teat program. To gati•fy 
early reporting requirements, a preliminary report •unarizing signifi— 
cant flight data vas published after each Of the 36 X—24B flights and 
distributed to all interested agencies. The X—24B program was a joint 
ef fort involving the Air Force Flight Dynamics Laboratory (APPDL) , the 
Air Force Plight Test Center and the National Aeronautics and Space 
Administration (NASA) Hugh L. Dryden Plight Re•earch Center. Program 
participation wag authorized by Project Directive 73—87 and van accæ— 
plished under Job Order Number 1366AO. 
The author wigheB to acknowledge the efforts Of Mr. Christopher J. 
Nagy for writing the computer program used to Calculate performance 
parameters from flight data and for developing the position error data 
in Appendix B.