6A series sections designed to eliminate trailing edge cusp which is characteristic of 6 series sections; theoretical data presented for 6A series basic thickness forms having position of minimum pressure at 30, 50, and 50% chord and with thickness ratios varying from 6 to 15% (published 1949, 20¢).


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    Title :

    Theoretical and experimental data for number of NACA 6A-series airfoil sections


    Additional title:

    Nat Advisory Committee Aeronautics -- Report


    Contributors:


    Publication date :

    1948


    Size :

    21 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :