Two dimensional wind tunnel tests were conducted on a high speed natural laminar flow airfoil in both the Langley 6 x 28 inch Transonic Tunnel and the Langley Low Turbulence Pressure Tunnel. The test conditions consisted of Mach numbers ranging from 0.10 to 0.77 and Reynolds numbers ranging from 3 x 1 million to 11 x 1 million. The airfoil was designed for a lift coefficient of 0.20 at a Mach number of 0.70 and Reynolds number of 11 x 1 million. At these conditions, laminar flow would extend back to 50 percent chord of the upper surface and 70 percent chord of the lower surface. Low speed results were also obtained with a 0.20 chord trailing edge split flap deflected 60 deg.


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    Titel :

    Wind Tunnel Results for a High-Speed, Natural Laminar-Flow Airfoil Designed for General Aviation Aircraft


    Beteiligte:
    W. G. Sewall (Autor:in) / R. J. McGhee (Autor:in) / J. K. Viken (Autor:in) / E. G. Waggoner (Autor:in) / B. S. Walker (Autor:in)

    Erscheinungsdatum :

    1985


    Format / Umfang :

    73 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch