Study dealing with design of efficient wings for supersonic aircraft used wings having sweepback of 50° at quarter-chord line, taper ratio of 0.20, NACA 65A005 thickness distribution, and aspect ratio of 3.5; tests were made at Reynolds number ranging from 1.2×106 to 3.6×106 through angle of attack range of -20 to 20°; analysis and comparison with theory presented.


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    Title :

    Effects at mach numbers of 1.61 and 2.01 of camber and twist on aerodynamic characteristics of three swept wings having same planform


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    48 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :