This paper describes experimental data obtained with a multi-element airfoil at flight Reynolds numbers and lift coefficients including Clmax. The wind tunnel test was conducted in the NASA Langley Low Turbulence Pressure Tunnel as part of a cooperative effort between McDonnell Douglas Aerospace and NASA Langley. The airfoil model is a supercritical design configured with a leading-edge slat and a single-segment trailing-edge flap. Data include surface static-pressure distributions (integrated to obtain lift), drag data obtained with wake-rake surveys, and fbwfield surveys obtained with a flat-tube and five-hole probe at nine stations on the configuration's upper surface. Effects of variations in Reynolds number and flap gap on airfoil performance and flowfield survey data are presented.


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    Title :

    Flowfield measurements about a multi-element airfoil at high Reynolds numbers


    Contributors:

    Conference:

    AIAA, Fluid Dynamics Conference ; 1993 ; Orlando, FL, United States


    Publication date :

    1993-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Flowfield measurements about a multi-element airfoil at high Reynolds numbers

    CHIN, VINCENT / PETERS, DAVID / SPAID, FRANK et al. | AIAA | 1993





    Supercritical Airfoil Flowfield Measurements

    Hurley, F.X. / Spaid, F.W. / Roos, F.W. et al. | AIAA | 1975