A wind tunnel investigation was conducted to study the application of supercritical technology to highly maneuverable combat aircraft. The configuration studied has a leading-edge sweep of 45 deg and an aspect ratio of 3.28. Two supercritical-wing shapes were tested at Mach numbers from 0.60 to 0.95 with angles of attack from -2 deg to 17 deg. On supercritical wing was designed to achieve a high level of transonic maneuver performance at a Mach number of 0.90; however, excessive flow separation developed on this wing at a Mach number of 0.85. A second supercritical wing was tested which had significantly reduced flow separation and improved drag characteristics at a Mach number of 0.85 and maintained the performance of the original wing at the higher Mach numbers. Leading-edge vortex generators did not improve the performance of the second wing; however, a sharp leading-edge flap produced sizable drag reductions at Mach numbers from 0.60 to 0.90.


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    Title :

    Supercritical Maneuvering Fighter Configuration. Wind-Tunnel Investigation at Mach Numbers of 0.60 to 0.95


    Contributors:
    M. J. Mann (author) / C. E. Mercer (author) / R. L. Campbell (author)

    Publication date :

    1982


    Size :

    69 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English