Previous analyses of boundary layer trailing edge noise for large rotors have used zero blade angle of attack as input data. Attention is presently given to the important effects of blade angle of attack changes on rotor trailing edge noise in the case of a UH-1 helicopter. The primary effect is in the low to mid-frequency range, where noise level increases with angle of attack.


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    Titel :

    Effect of angle of attack on rotor trailing-edge noise


    Beteiligte:
    Chou, S.-T. (Autor:in) / George, A. R. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1984



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Effect of angle of attack on rotor trailing-edge noise

    CHOU, S.-T. / GEORGE, A. R. | AIAA | 1984


    Helicopter rotor trailing edge noise

    SCHLINKER, R. / AMIET, R. | AIAA | 1981


    Effects of Angle of Attack and Velocity on Trailing Edge Noise

    Hutcheson, F. V. / Brooks, T. F. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2004


    Effects of Angle of Attack and Velocity on Trailing Edge Noise

    Hutcheson, Florence / Brooks, Thomas | AIAA | 2004


    Effects of Angle of Attack and Velocity on Trailing Edge Noise

    Hutcheson, Florence V. / Brooks, Thomas F. | NTRS | 2004