An 11.43-percent-thick airfoil, the S407, 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 two primary objectives of high maximum lift and low profile drag have been achieved. The constraints on the pitching moment and the airfoil thickness have been satisfied. The airfoil exhibits a sharp stall, which does not meet the design objective. Comparisons of the theoretical and experimental results generally show good agreement.


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    Title :

    Design and Experimental Results for the S407 Airfoil


    Contributors:

    Publication date :

    2010


    Size :

    88 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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