Relation between trailing edge noise and boundary layer instability

Yasufumi Konishi, Shohei Takagi, Takuji Kurotaki, Yasuaki Kohama, Takuma Kato

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    The purpose of the present paper is to show the acoustic feedback loop plays an important role on the frequency-selection mechanism of the tonal noise emanated from the trailing-edge of 2-D wing. For raveling the frequency-selection mechanism, a thin splitter plate placed behind the trailing edge is used to suppress the tonal noise and then an artificial acoustic disturbance by means of loud speaker is introduced into the flow. The experimental result shows that acoustic feedback loop contributes to generation of the discrete T-S wave. Further experiment lso shows that boundary layer only accepts acoustic disturbance with favorable frequency, which results in the step-like structures against the distance between speaker and wing model.

    Original languageEnglish
    Title of host publicationICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
    Pages3365-3371
    Number of pages7
    Volume2
    Publication statusPublished - 2008 Dec 1
    Event26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008 - Anchorage, AK, United States
    Duration: 2008 Sep 142008 Sep 19

    Other

    Other26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008
    CountryUnited States
    CityAnchorage, AK
    Period08/9/1408/9/19

    Keywords

    • Acoustic feedback
    • Boundary-layer transition
    • Trailing-edge noise

    ASJC Scopus subject areas

    • Aerospace Engineering
    • Control and Systems Engineering
    • Electrical and Electronic Engineering
    • Materials Science(all)

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  • Cite this

    Konishi, Y., Takagi, S., Kurotaki, T., Kohama, Y., & Kato, T. (2008). Relation between trailing edge noise and boundary layer instability. In ICAS Secretariat - 26th Congress of International Council of the Aeronautical Sciences 2008, ICAS 2008 (Vol. 2, pp. 3365-3371)