6A-series airfoil sections designed to eliminate trailing edge cusp characteristic of NACA 6-series sections; data presented for NACA 6A-series basic thickness forms having position of minimum pressure at 30, 40, and 50% chord and with thickness ratios varying from 6 to 15%.


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    Title :

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


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1947


    Size :

    14 pages


    Remarks:

    29 Supp Sheets


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :