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.


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    Title :

    Preliminary flight and wind tunnel comparisons of the inlet/airframe interaction of the F-15 airplane


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA


    Publication date :

    1979-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English






    Flight and wind-tunnel comparisons of the inlet-airframe interaction of the F-15 airplane

    Webb, L. D. / Andriyich-Varda, D. / Whitmore, S. A. | NTRS | 1984


    Flight and Wind-Tunnel Comparisons of the Inlet-Airframe Interaction of the F-15 Airplane

    L. D. Webb / D. Andriyich-varda / S. A. Whitmore | NTIS | 1984


    Airframe-inlet integration

    HILL, P. | AIAA | 1970