An experimental investigation was conducted in an 11- by 11-foot transonic wind tunnel to study the lift, drag and stability characteristics of a 0.087-scale model of an operational airplane fitted with an oblique wing. The model wing was of elliptical planform with an unswept aspect ratio of 12.7 and a thickness of 10 percent. All other external geometric features of the model were scaled to the basic full size operational airplane with the engine inlet faired closed. Longitudinal and lateral-directional stability data were obtained with the wing at sweep angles of 0 deg, 45 deg and 60 deg Test Mach numbers ranged from 0.6 to 1.4 deg Angles of attack were between minus 4 deg and 8 deg at zero sideslip. Angles of sideslip were between plus and minus 4 degrees for two angles of attack depending upon the wing configuration. Tests were conducted at a Reynolds number of 6 million per foot except for a few runs when balance capacity limited the Reynolds number to 4 million per foot.


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    Title :

    Wind tunnel tests of an F-8 airplane model equipped with an oblique wing


    Contributors:

    Publication date :

    1973-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Wind Tunnel Tests of an F-8 Airplane Model Equipped with an Oblique Wing

    L. A. Graham / R. T. Jones / J. L. Summers | NTIS | 1973





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