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    Title :

    A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2. : Wing-fuselage Configuration Having a Wing of 0 Degrees Sweepback, Aspect Ratio 4.0,taper Ratio 0.6, and NACA 65A006 Ai


    Contributors:

    Publication date :

    1951-03-06


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English