Preliminary flight and wind tunnel comparison data are presented for the F-15 inlet/airframe interactions program. Test conditions and instrumentation for both the model and the aircraft are described. Flight and wind tunnel inlet drag data (for a 0-deg angle of attack and Mach numbers of 0.6, 0.9, and 1.2), derived by using nearly identical pressure integration equations, are compared. The effects of a movable cowl, movable ramps, and other system components on pressure flow fields along the airframe are discussed. Excellent agreement between wind tunnel and flight pressure-integrated drags is found at all three Mach numbers. The wind tunnel data show good agreement for pressure-integrated and force-balance-measured inlet drag, except at Mach 0.6. Flight-measured pressure-integrated inlet lift is lower than that measured in the wind tunnel.
Preliminary flight and wind tunnel comparisons of the inlet/airframe interaction of the F-15 airplane
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA
1979-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
AIAA | 1970
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