This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent.


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    Titel :

    Wind tunnel tests on airfoil boundary control using a backward opening slot


    Beteiligte:

    Erscheinungsdatum :

    01.10.1929


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch