Semispan wing models were tested in Langley supersonic tunnel at Re from 1.9×106 to 6.5×106 based on mean geometric chord; complex wing forms with thickened roots, extended root chords, and higher volumes show lower zero lift wave drags than plain swept wings.


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    Title :

    Characteristics at mach number of 2.03 of series of wings having various spanwise distributions of thickness ratio and chord


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1960


    Size :

    26 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :