The low speed aerodynamic characteristics of a 14 percent thick supercritical airfoil are documented. The wind tunnel test was conducted in the Low Turbulence Pressure Tunnel. The effects of varying chord Reynolds number from 2,000,000 to 18,000,000 at a Mach number of 0.15 and the effects of varying Mach number from 0.10 to 0.32 at a Reynolds number of 6,000,000 are included.


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    Titel :

    Low-Speed Aerodynamic Characteristics of a 14-Percent-Thick NASA Phase 2 Supercritical Airfoil Designed for a Lift Coefficient of 0.7


    Beteiligte:
    C. D. Harris (Autor:in) / R. J. Mcghee (Autor:in) / D. O. Allison (Autor:in)

    Erscheinungsdatum :

    1980


    Format / Umfang :

    104 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch