Tests made in NACA 4 by 6-ft vertical tunnel; section data suitable for application to design of horizontal and vertical tail surfaces were obtained.


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    Title :

    Pressure-distribution investigation of N.A.C.A. 0009 airfoil with 80-percent-chord plain flap and three tabs


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1940


    Size :

    11 pages


    Remarks:

    23 Supp plates, Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :