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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    Titel :

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


    Beteiligte:
    C. D. Harris (Autor:in) / C. W. Brooks (Autor:in) / P. G. Clukey (Autor:in) / J. P. Stack (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    121 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch