Wind tunnel tests in Langley low turbulence pressure tunnel to obtain data of importance for rotary wing aircraft in view of fact that recent trends toward higher forward speeds have resulted in increases in area of very high angle-of-attack region, and forces contributed by this region constitute greater part of total rotor forces than in past.


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    Titel :

    Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0° to 180°


    Weitere Titelangaben:

    NACA -- Tech Note


    Beteiligte:
    Critzos, C.C. (Autor:in) / Heyson, H.H. (Autor:in) / Boswinkle, Jr., R.W. (Autor:in)


    Erscheinungsdatum :

    1955


    Format / Umfang :

    21 pages


    Medientyp :

    Report


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0° to 180°

    Critzos, Chris C. / Heyson, Harry H. / Boswinkle, Robert W. | TIBKAT | 1955


    Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees

    Critzos, Chris C / Heyson, Harry H / Boswinkle, Robert W , Jr | NTRS | 1955




    Experimental aerodynamic characteristics of an NACA 0012 airfoil with simulated ice

    KORKAN, K. D. / CROSS, E. J. / CORNELL, C. C. | AIAA | 1985