A 14-percent-thick airfoil, the S411, intended for rotorcraft applications has been designed and analyzed theoretically and verified experimentally in The Pennsylvania State University Low-Speed, Low-Turbulence Wind Tunnel. The airfoil incorporates a 5-percent-chord tab. The two primary objectives of high maximum lift and low profile drag have been achieved. The constraint on the pitching moment has been exceeded; that on the airfoil thickness, satisfied. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement. Comparisons with the S406 airfoil confirm the achievement of the objectives.


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    Title :

    Design and Experimental Results for the S411 Airfoil


    Contributors:

    Publication date :

    2010


    Size :

    76 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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