Low speed wind tunnel tests were conducted to evaluate the effects on performance of modifying a 23 percent thick low speed airfoil. The airfoil contour was altered to reduce the upper-surface adverse pressure gradient and hence reduce boundary layer separation. The chord Reynolds number varied from about 2,000,000 to 9,000,000.


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    Title :

    Wind-Tunnel Results for an Improved 21-Percent-Thick Low-Speed Airfoil Section


    Contributors:

    Publication date :

    1978


    Size :

    47 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English