The impingement of a broken-down vortex is well-known as physical mechanism of buffeting of the tail of an F-series aircraft. This interaction may be associated with several forms of unsteadiness: nonperiodic displacements of the entire vortex core, a helical-mode instability of the broken-down vortex, and streamwise fluctuations of the region of vortex breakdown. Particularly relevant to the present investigation are the works of Washburn et al. (AIAA Paper 93-050, Jan 1993) and Canbazoglu et al. (Journal of Aircraft, Vol. 29, No. 6, 1992, pp. 986-992). Both of these investigations detected not only a primary (incident) vortex along the tail, but also a secondary (counter) vortex that was generally attributable to some type of vortex generation in the leading region of the tail; the physics of the onset of the secondary vortex, however, were not addressed. Although certain aspects of the fluctuating vorticity field were preliminarily characterized by Canbazoglu et al., the fluctuating velocity fields, which are essential for characterizing the origin of buffet loading of the tail, have not been addressed. Furthermore, the physical origin of these velocity fluctuations is intimately related to the Reynolds stress, which also has not been provided. The aim of this investigation is to address these unclarified issues and to interpret them physically using a technique of high-image- density particle image velocimetry. Experiments were performed in a large-scale water channel to allow effective imaging of the flow structure around the delta wing-tail model arrangement. A technique of high-image-density particle image velocimetry was used to determine the instantaneous velocity field at effective frame rate of 15 frames per second. These velocity fields were determined over four sequential crossflow planes located at different streamwise distances from the primary vortex breakdown location. The time-averaged representations of vorticity and velocity show that the physical mechanism for generation of the secondary vortex mentioned above is separation from the edge of the tail. Near the leading region of the tail, the primary-secondary (counter) vortex system is highly coherent. The instantaneous vortex patterns deviate only slightly from the time-averaged representations. Furthermore, locations of peak values of velocity fluctuation and Reynolds stress occur at the interface between the primary and secondary vortices on the outboard side of the tail. Evolution of this vortex pattern along the tail is associated with a degeneration of coherence of the primary-secondary vortex system. That is, the instantaneous states deviate significantly from the time-averaged pattern of the primary-secondary vortex System. In the trailing region of the tail, peak values of velocity fluctuation and Reynolds stress are still detectable at the interface between the primary and secondary vortex on the outboard side of the tail. However, in addition, severe distortion of the primary vortex about the tail results in additional peaks of velocity fluctuation and Reynolds stress on the inboard side.


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    Titel :

    Vortex breakdown - Tail interaction


    Weitere Titelangaben:

    Wechselwirkung des aufplatzenden Wirbels über einem Deltaflügel mit dem Flugzeugleitwerk


    Beteiligte:
    Kim, Y. (Autor:in) / Ozgoren, M. (Autor:in) / Rockwell, D. (Autor:in)

    Erschienen in:

    AIAA Journal ; 41 , 3 ; 544-549


    Erscheinungsdatum :

    2003


    Format / Umfang :

    6 Seiten, 5 Bilder, 16 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch





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