Report supplements information presented previously (see reference to NACA -- TN 1368, by L.K.LOFTIN, Jr, in Engineering Index 1947 p 25), and provides ordinates of additional airfoil sections useful in design of supersonic aircraft; simplified procedure for obtaining pressure distributions about airfoil sections of intermediate thicknesses.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Ordinates and theoretical pressure-distribution data for NACA 6- and 6a-series airfoil sections with thicknesses from 2 to 21 and from 2 to 15 percent chord, respectively


    Additional title:

    NACA -- Tech Note


    Contributors:


    Publication date :

    1958


    Size :

    99 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :