Wind tunnel experiments were conducted to investigate the effect of vortex generators on a transonic corner flow separation, resulting from the interaction of a normal shock wave with a turbulent boundary layer in a duct at M = 1.4 . The shape of the vortex generators was rectangular. The vortex generators were mounted on the bottom wall of the test section. The investigation studied the effects of the rotation direction of the vortex, the vortex generator size and position relative to the shock, and the walls. When the leading edge of the vortex generators turned toward the corner, the effect of the vortex generators on the corner flow separation monotonically decreased as the vortex generators size reduced. In these cases, it was observed that independent separations appeared on the bottom wall. When the leading edge of the vortex generators pointed in the opposite direction away from the corner, the flow structure was found to depend on the size and the location of the vortex generators. The flow structures were categorized into three modes. The effect of the vortex generators and the three modes were successfully collapsed with a location parameter normalized by the second power of the nondimensional size.


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    Titel :

    Vortex Generators for Corner Separation Caused by Shock-Wave/Boundary-Layer Interactions


    Beteiligte:

    Erschienen in:

    Journal of Aircraft ; 56 , 1 ; 239-249


    Erscheinungsdatum :

    2018-09-13


    Format / Umfang :

    11 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch