Airfoil trailing-edge noise up to a Reynolds number based on chord of 2.96 x 10 to the 6th power was studied. Comparisons are made with current theory, particularly with regard to the nature of the pressure field in the vicinity of the trailing-edge and its influence on the radiated noise.


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    Title :

    An experimental investigation of trailing-edge noise


    Contributors:

    Publication date :

    1979-06-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


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