Wind-tunnel tests were conducted to evaluate the effects on performance of modifying a 13-percent-thick low-speed airfoil. The airfoil contour was altered to reduce the aft upper surface pressure gradient and hence delay boundary layer separation at typical lift coefficients for light general aviation airplanes. The tests were conducted at a Mach number of 0.15 or less over a Reynolds number range from about 1,000,000 to 9,000,000.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Low-Speed Wind Tunnel Results for a Modified 13-Percent-Thick Airfoil


    Beteiligte:
    R. J. Mcghee (Autor:in) / W. D. Beasley (Autor:in)

    Erscheinungsdatum :

    1977


    Format / Umfang :

    40 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch