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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Design and Experimental Results for the S407 Airfoil


    Beteiligte:
    D. M. Somers (Autor:in) / M. D. Maughmer (Autor:in)

    Erscheinungsdatum :

    2010


    Format / Umfang :

    88 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Design and Experimental Results for the S414 Airfoil

    D. M. Somers / M. D. Maughmer | NTIS | 2010


    Design and Experimental Results for the S415 Airfoil

    D. M. Somers / M. D. Maughmer | NTIS | 2010


    Design and Experimental Results for the S406 Airfoil

    D. M. Somers / M. D. Maughmer | NTIS | 2010


    Design and Experimental Results for the S411 Airfoil

    D. M. Somers / M. D. Maughmer | NTIS | 2010