Data obtained at six spanwise stations of wing; pressure plots presented for Mach number range from 0.20 to 0.60 and for angle of attack range from -4° to stalling angle of attack.


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    Title :

    Chordwise pressure distributions on 12-foot-span wing of NACA 66-series airfoil sections up to Mach number of 0.60


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:
    Wall, N.E. (author)


    Publication date :

    1948


    Size :

    147 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :