It is pointed out that an accurate prediction of the high-speed impulsive rotor noise is very difficult since the noise field depends on many complex factors. Schmitz and Yu (1981) have conducted a study with the aim to include local aerodynamic nonlinearities in a calculation regarding the acoustic shock. In the present investigation, the hover case of the model rotor studied by Schmitz and Yu was recomputed without certain implicit assumptions made in the earlier calculation. The obtained results show that the Schmitz-Yu computations are very much base-support area dependent. Attention is given to the quadrupole integral, and the pressure-time curves for the model rotor in hover.


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    Titel :

    The calculation of transonic rotor noise


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    01.07.1984



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    The calculation of transonic rotor noise

    Aggarwal, H.R. | Tema Archiv | 1984


    The calculation of transonic rotor noise

    AGGARWAL, H. R. | AIAA | 1984




    Unsteady Analysis of Transonic Helicopter Rotor Noise

    Aoyama, T. / Kawachi, K. / Kamio, J. et al. | British Library Conference Proceedings | 1993