Pressure measurements were obtained at Mach numbers from 0.80 to 1. 05; results indicate that highly swept shock originates at wing leading edge body juncture and has large influence on loading over inboard wing sections.


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    Title :

    Investigation at transonic speeds of loading over 45° swept-back wing having aspect ratio of 3, taper ratio of 0.2, and NACA 65a004 airfoil sections


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    93 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :