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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    Title :

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


    Additional title:

    NACA -- Tech Note


    Contributors:


    Publication date :

    1955


    Size :

    21 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    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