A profile from the NASA General Aviation Whitcomb series and NACA profiles are used as a starting point in designing an advanced airfoil for general aviation aircraft. Potential theory pressure distribution calculations, together with boundary layer calculations, permit a decrease in the null moment and an optimization of the lift characteristics of the wing. Trailing edge flap design is also improved. Wind tunnel tests are used to compare the conventional profiles, the NASA profile, and the improved design.


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    Title :

    Profile design for an advanced-technology airfoil for general aviation aircraft


    Contributors:
    Welte, D. (author)

    Publication date :

    1978-08-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :