Potential theory of the pressure distribution on a wing section shall always give the values bigger than the ones obtained from the experiments in a viscous flow. It comes from the viscous effect due to the boundary layer around a wing section. The boundary layer on the suction side of a wing section grows thicker than the one on the pressure side, when the wing section has some angle of attack against a viscous flow. Such unequality in the boundary layer thickness hydrodynamically brings the virtual reduction of the attack angle as well as the camber ratio of a wing section due to the decline of the nose-tail line, or effectively distorts the section shape so that the trailing edge should be slightly raised up from the original. The author proposes a practical method to form the distorted wing section, in which the experimental slope of lift curve is utilized, and by which the pressure distribution can be computed for a wing section in a real flow. The pressure distribution thus computed for an exemplified wing section is in rather good agreement with the experimental result. (Wassmann)


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    Title :

    A method to compute the pressure distribution on a wing section, using the experimental slope of lift curve


    Additional title:

    Methode zur Berechnung der Druckverteilung in einem Fluegelbereich mit Hilfe der experimentell ermittelten Steigung der Sogkurve


    Contributors:
    Mori, M. (author)


    Publication date :

    1980


    Size :

    7 Seiten, 7 Bilder, 13 Quellen


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English