A wind tunnel test of a generic fighter configuration was tested in the National Transonic Facility through a cooperative agreement between NASA Langley Research Center and McDonnell Douglas. The primary purpose of the test was to assess Reynolds number scale effects on a thin-wing, fighter-type configuration up to full-scale flight conditions (that is, Reynolds numbers of the order of 60 million). The test included longitudinal and lateral/directional studies at subsonic and transonic conditions across a range of Reynolds numbers from that available in conventional wind tunnels to flight conditions. Results are presented for three Mach numbers (0.6, 0.8, and 0.9) and three configurations: (1) Fuselage/Wing; (2) Fuselage/Wing/Centerline Vertical Tail/Horizontal Tail; and (3) Fuselage/Wing/Trailing-Edge Extension/Twin Vertical Tails. Reynolds number effects on the longitudinal aerodynamic characteristics are presented herein.


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    Title :

    Investigation of Reynolds Number Effects on a Generic Fighter Configuration in the National Transonic Facility


    Contributors:
    Tomek, W. G. (author) / Hall, R. M. (author) / Wahls, R. A. (author) / Luckring, J. M. (author) / Owens, L. R. (author)

    Conference:

    40th AIAA Aerospace Sciences Meeting and Exhibit ; 2002 ; Reno, NV, United States


    Publication date :

    2002-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :