Wave drag equations derived for rhombic-profile tapered wings with maximum thickness line swept less than Mach lines; variations in drag with taper ratio, aspect ratio, sweepback, and Mach number determined; calculations presented for representative plan forms and for family of wings having equal root bending stress.


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    Title :

    Supersonic wave drag of nonlifting sweptback tapered wings with Mach lines behind line of maximum thickness


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1948


    Size :

    34 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :