Pressure-distribution measurements were made on the wing of a fighter-type airplane to determine the span loading and to compare center-of-pressure results with those obtained by strain-gage measure¬ments on the same airplane during a previous flight investigation. The flight tests were all made at a pressure altitude of about 30,000 feet and covered a Mach number range from approximately 0.35 to 0.81. Available wind-tunnel pressure-distribution data for a prototype of the test airplane are also included for comparison. Both flight and wind-tunnel pressure-distribution data are separated into additional and basic air load components.
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