Characterization of flight vehicle unsteady aerodynamics is often studied via large scale wind tunnel testing. Boundary layer noise is measured by miniature pressure transducers installed in a model. Noise levels (2-5 dB ref. 20 ?Pa) can be induced when transducer is mounted out of flush with model outer surface. This effect must be minimized to accurately determine aerodynamically induced acoustic environments.


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    Titel :

    Reducing the Effect of Transducer Mount Induced Noise (XMIN) on Aeroacoustic Wind Tunnel Testing Data with a New Transducer Mount Design


    Beteiligte:
    Herron A. J. (Autor:in) / Reed D. K. (Autor:in) / Nance D. K. (Autor:in)

    Erscheinungsdatum :

    2015


    Format / Umfang :

    25 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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