Six 3-inch-chord symmetrical air foils for propeller shanks having thickness ratios from 15 to 40 percent chord were tested at high subsonic Mach numbers. Schlieren photographs of each airfoil showed the flow characteristics to be very erratic at low supercritical speeds but improved at the highest supercritical speeds tested. Normal-force coefficients for the thick airfoils were very erratic at subcritical speeds but became regular at supercritical Mach numbers. The significant factor in improving airfoil performance was found to be the reduction of model thickness ratios.


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    Titel :

    Effects of Compressibility on the Flow Past Thick Airfoil Sections


    Beteiligte:
    B. N. Daley (Autor:in) / M. D. Humphreys (Autor:in)

    Erscheinungsdatum :

    1948


    Format / Umfang :

    48 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Effects of compressibility on flow past thick airfoil sections

    Daley, B.N. / Humphreys, M.D. | Engineering Index Backfile | 1948


    Effects of Compressibility on the Flow past Thick Airfoil Sections

    Daley, Bernard N / Humphreys, Milton D | NTRS | 1948


    Effects of compressibility on the flow past thick airfoil sections

    Daley, Bernard N. / Humphreys, Milton D. | TIBKAT | 1948



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