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    A comparison of computer-generated lift and drag polars for a Wortmann airfoil to flight and wind tunnel results (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA-CR-176963 , NAS 1.26:176963
    Format: application/pdf
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