High performance aircraft exploit vortex flows for enhanced maneuverability and control. Streamwise vortices, which are generated at various locations on the aircraft, can interact with fins and tails, and result in flow-induced vibration. This investigation addresses the impingement of a streamwise vortex on a thin plate. Breakdown of the incident vortex generates vortical structures that are distorted at the leading-edge. The nature of this distortion is repressented by instantaneous velocity and vorticity distributions over entire planes adjacent to the plate. The instantaneous distributions of vorticity show well-defined, large-scale concentrations along the boundary of the breakdown region, nominally located along the locus of maximum averaged vorticity. Correspondingly, the amplitudes of the surface pressure spectra at the leading-edge of the plate are largest when the location of maximum vorticity is aligned with the edge. The dominant frequency of the surface pressure on the plate is, however, insensitive to offset of the vortex axis relative to the leading-edge of the plate. On the other hand, global fluctuations of the entire region of vortex breakdown are sensitive to the offset of the incident vortex.


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    Title :

    Buffeting at the leading-edge of a flat plate due to a streamwise vortex: flow structure and surface pressure loading


    Additional title:

    Durch Strömungswirbel an der Vorderkante einer flachen Platte verursachte Stoßerscheinungen: Strömungsstruktur und Oberflächendruckbelastung


    Contributors:
    Wolfe, S. (author) / Lin, J.C. (author) / Rockwell, D. (author)

    Published in:

    Publication date :

    1995


    Size :

    12 Seiten, 9 Bilder, 14 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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