The effects of deployment angle and size of symmetrically mounted upper-surface and lower-surface spoilers on the flutter characteristics of a simple, paddle-like, low-aspect-ratio, rectangular wing model that was tested at Mach number 0.80 in the Langley Transonic Dynamics Tunnel are presented. The results show that the flutter dynamic pressure is increased by increasing either spoiler deployment angle or spoiler size. For the configurations studied spoiler size was more effective than deployment angle in increasing the flutter dynamic pressure.


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    Titel :

    Some Effects of Aerodynamic Spoilers on Wing Flutter


    Beteiligte:
    R. V. Doggett (Autor:in)

    Erscheinungsdatum :

    1989


    Format / Umfang :

    18 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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