Shock drag of sweptback wing originates mainly from roots, where "S" shaped wing streamlines are constrained to move along side of fuselage; accurate method of calculating free stream shape of these streamlines, used to design model of fairing for EC.1240 wing sweptback 65° from flat plate.


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    Title :

    Tests of fairing to reduce drag of supersonic swept-wing root


    Additional title:

    J Aeronautical Sciences


    Contributors:


    Publication date :

    1955


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :