Tunnel tests to obtain characteristics of control surfaces; symmetrical double wedge airfoil of 7% thickness, with 15 and 30% trailing edge flaps, used as model; pressure measurements and Schlieren photographs taken in two-dimensional channel at Mach numbers 1.38, 1.48 and 1.58.


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    Title :

    Supersonic tests of conventional control surfaces on double-wedge airfoil


    Additional title:

    J Aeronautical Sciences


    Contributors:


    Publication date :

    1950


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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