The effects of Mach number and Reynolds number on the experimental surface pressure distributions and transition patterns for a large chord, swept supercritical airfoil incorporating an active Laminar Flow Control suction system with spanwise slots are presented. The experiment was conducted in the Langley 8 foot Transonic Pressure Tunnel. Also included is a discussion of the influence of model/tunnel liner interactions on the airfoil pressure distribution. Mach number was varied from 0.40 to 0.82 at two chord Reynolds numbers, 10 and 20 x 1,000,000, and Reynolds number was varied from 10 to 20 x 1,000,000 at the design Mach number.


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    Title :

    NASA (National Aeronautics and Space Administration) Langley Laminar-Flow-Control Experiment on a Swept Supercritical Airfoil: Basic Results for Slotted Configuration


    Contributors:
    C. D. Harris (author) / C. W. Brooks (author) / P. G. Clukey (author) / J. P. Stack (author)

    Publication date :

    1989


    Size :

    121 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English