The noise generated from a 1/4-scale AH-1G helicopter configuration was investigated in the Langley V/STOL tunnel. Microphones were installed in positions scaled to those for which flight test data were available. Model and tunnel conditions were carefully set to properly scaled flight conditions. Data presented indicate a high degree of similarity between model and flight test results. It was found that the pressure time history waveforms are very much alike in shape and amplitude. Blade slap when it occurred seemed to be generated in about the same location in the rotor disk as on the flight vehicle. If model and tunnel conditions were properly matched, including inflow turbulence characteristics, the intensity of the blade-slap impulse seemed to correlate well with flight.


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    Titel :

    Helicopter noise research at the Langley V/STOL tunnel


    Beteiligte:
    Hoad, D. R. (Autor:in) / Green, G. C. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.08.1978


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Trends in Langley helicopter noise research

    Hubbard, H. H. / Maglieri, D. J. / Stephens, D. G. | NTRS | 1978





    Recent Langley helicopter acoustics contributions

    Morgan, Homer G. / Pao, S. P. / Powell, C. A. | NTRS | 1988