The attention is focused on rotor blades thickness noise (flow subsonic everywhere). The solution of the wave equation is written in a closed form (frequency domain), which emphasizes the essential parameters for this field. On an other side, starting from an estimation of the loads on the rotor disk (lifting line theory), the acoustic emission due to loads is estimated in such a way that we can compare the acoustic efficiency of blade thickness and loads. To compare experimental results and predictions, an original signal processing method was designed, which compensates the doppler effect due to the helicopter motion. (Krautzig)


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    Titel :

    Helicopter rotor thickness noise


    Weitere Titelangaben:

    Rotorlaerm vom Hubschrauber, abhaengig von der Rotorblattstaerke


    Beteiligte:
    Dahan, C. (Autor:in) / Gratieux, E. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1980


    Format / Umfang :

    10 Seiten, 18 Bilder, 11 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Helicopter rotor thickness noise

    DAHAN, C. / GRATIEUX, E. | AIAA | 1980


    Helicopter Rotor Thickness Noise

    Claude Dahan / Edmond Gratieux | AIAA | 1981



    Helicopter tail rotor noise

    CHOU, S.-T. / GEORGE, A. | AIAA | 1986


    Helicopter rotor noise generation.

    Leverton, J. W. / Wright, S. E. | NTRS | 1969