Shock structure modified to eliminate associated noise. Shock wave repeats in supersonic flow adjoining subsonic flow layer. When supersonic layer is added, shock wave is partially transmitted at interface. Result is almost total elimination of shock pattern after one or two reflections. Technique applicable to inverted as well as to normal-velocity-profile coannular jets and used to eliminate or reduce shock noise of turbojet engines.


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    Title :

    Reduced Aircraft-Engine Noise


    Contributors:
    Tanna, H. K. (author) / Brown, W. H. (author) / Tam, C. K. (author)

    Published in:

    Publication date :

    1983-08-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


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