Contour corrections, small in comparison with boundary-layer thickness, produce flow changes which cannot be adequately described by simple theory of characteristics; procedure involving use of experimentally determined jack influences was successfully applied to correction of nozzle profiles in 12-in. supersonic wind tunnel; considerations of further application of this method.


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    Title :

    Correction of flexible plate supersonic nozzle contours by influence methods


    Additional title:

    J Aeronautical Sciences


    Contributors:

    Published in:

    Publication date :

    1955


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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