The maximum obtainable airfoil profile thickness for the simplest supercritical roof-top pressure distributions was determined using systematic exemplary calculations with the profile design method based on the integral method. These thick profiles with shock-free supercritical flow are especially suitable for application to transport aircraft. The maximum thickness limits found are in good agreement with empirical estimations.


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    Title :

    The Thickness Distribution of Profiles for Shock-Free Flow Without Lift Untersuchungen ueber die Dickenverteilung von Profilen bei Stossfreier Umstroemung Ohne Auftrieb


    Contributors:
    H. Hansen (author)

    Publication date :

    1977


    Size :

    26 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English