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    Wind tunnel test of a fighter aircraft wing/store flutter suppression system: An international effort

    Wind tunnel test of a fighter aircraft wing/store flutter suppression system: An international effort


    A 30% scale, half span model of a lightweight fighter aircraft with an active wing/store flutter suppression system was tested in the NASA Langley Research Center sixteen foot transonic dynamics tunnel. The test featured a store configuration that was intentionally designed to exhibit a violent flutter condition. In addition to Northrop organized control laws, three European countries also contributed control laws to stabilize this condition. After the control laws were mechanized by Northrop, they were tested at the Langley facility. The model was tested up to 170% of the open loop flutter dynamic pressure in a number of cases, with the indication that a substantially greater improvement was achievable. Some special features of the test model are discussed and the design and implementation of the control laws as well as the test monitoring techniques and results are presented.

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    Titel :

    Wind tunnel test of a fighter aircraft wing/store flutter suppression system: An international effort

    Beteiligte:
    Hwang, C. (Autor:in) / Johnson, E. H. (Autor:in) / Mills, G. R. (Autor:in) / Noll, T. E. (Autor:in) / Farmer, M. G. (Autor:in)
    Erschienen in:

    AGARD Rept. on a Coop. Programme on Active Flutter Suppression

    Erscheinungsdatum :

    1980-08-01

    Medientyp :

    Aufsatz (Konferenz)

    Format :

    Keine Angabe

    Sprache :

    Englisch

    Schlagwörter :

    Aircraft Stability And Control

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