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


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    Title :

    A comparison of computer-generated lift and drag polars for a Wortmann airfoil to flight and wind tunnel results


    Contributors:

    Publication date :

    1984-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :