Results of tests of new wing section, N A C A 23012, at Reynolds numbers between 1,000,000 and 8,000,000; new airfoil develops reasonably high maximum lift and low profile drag, resulting in unusually high value of speed-range index; pitching-moment coefficient is very small. (Price 5¢)


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    Title :

    Characteristics of N.A.C.A. 23012 airfoil from tests in full-scale and variable-density tunnels


    Additional title:

    Nat Advisory Committee Aeronautics -- Report


    Contributors:
    Jacobs, E.N. (author) / Clay, W.C. (author)


    Publication date :

    1935


    Size :

    10 pages


    Remarks:

    Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :