A 14.12-percent-thick, natural-laminar-flow airfoil, the S415, intended for the rotor of a helicopter in hover 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 constraint on the pitching moment has been satisfied. The airfoil exhibits a docile stall. Comparisons of the theoretical and experimental results generally show good agreement.


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    Title :

    Design and Experimental Results for the S415 Airfoil


    Contributors:

    Publication date :

    2010


    Size :

    60 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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