An exploratory flow visualization study conducted in the Langley Vortex Research Facility to investigate the effectiveness of lateral control surface oscillations as a potential method for wake vortex attenuation on a 0.03 scale model of a wide body jet transport aircraft is described. Effects of both asymmetric surface oscillation (control surfaces move as with normal lateral control inputs) and symmetric surface oscillation (control surfaces move in phase) are presented. The asymmetric case simulated a flight maneuver which was previously investigated on the transport aircraft during NASA/FAA flight tests and which resulted in substantial wake vortex attenuation. Effects on the model wake vortex systems were observed by propelling the model through a two dimensional smoke screen perpendicular to the model flight path. Results are presented as photographic time histories of the wake characteristics recorded with high speed still cameras. Effects of oscillation on the wake roll up are described in some detail, and the amount of vortex attenuation observed is discussed in comparative terms. Findings were consistent with flight test results in that only a small amount of rotation was observed in the wake for the asymmetric case. A possible aerodynamic mechanism contributing to this attenuation is suggested.


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    Titel :

    Flow visualization of the wake of a transport aircraft model with lateral-control oscillations


    Beteiligte:

    Erscheinungsdatum :

    1983-06-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Aircraft Wake Vortex Transport Model

    M. R. Brashears / James N. Hallock | AIAA | 1974


    Aircraft wake vortex transport model

    BRASHEARS, M. / HALLOCK, J. | AIAA | 1973




    Supersonic wake flow visualization

    HALL, JR., C. / MUELLER, T. / SULE, W. | AIAA | 1969