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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Effects of Compressibility on the Flow Past Thick Airfoil Sections


    Contributors:

    Publication date :

    1948


    Size :

    48 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    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



    Compressibility Effects in Airfoil Secondary Tones

    Rodarte Ricciardi, Tulio / Wolf, William / Taira, Kunihiko | AIAA | 2021