Computations of drag polars for a low-speed Wortmann sailplane airfoil are compared with both wind tunnel and flight test results. Excellent correlation was shown to exist between computations and flight results except when separated flow regimes were encountered. Smoothness of the input coordinates to the PROFILE computer program was found to be essential to obtain accurate comparisons of drag polars or transition location to either the flight or wind tunnel flight results.


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    Title :

    Comparison of Wortmann Airfoil Computer-Generated Lift and Drag Polars with Flight and Wind Tunnel Results


    Contributors:
    A. H. Bowers (author) / A. G. Sim (author)

    Publication date :

    1984


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English