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      Interaction of a Backward-Facing Step and Crossflow Instabilities in Boundary-Layer Transition

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          Abstract

          A swept flat plate model with an imposed pressure gradient was experimentally investigated in a low-speed flow to determine the effect of a backward-facing step on transition in a stationary crossflow–dominated flow. Detailed hotwire measurements of boundary-layer flow were performed to investigate the upstream shift in transition due to a step height of 49% of the local unperturbed boundary-layer thickness. Increasing the initial stationary crossflow amplitude caused an upstream movement of the transition front for the backward-facing step case. The step caused a local increase in the growth of the stationary crossflow instabilities, but the stationary crossflow amplitude at transition was sufficiently low ( < 0.04 U e ) so that stationary crossflow was not solely responsible for transition. The unsteady velocity spectra downstream of the step were rich with unsteady disturbances in the 80- to 1500-Hz range. Three distinct families of disturbances were identified based on phase speed and wave angle, namely, a highly oblique disturbance (possibly traveling-crossflow-like), a Tollmien–Schlichting-wave-like disturbance, and a shear-layer instability. The stationary crossflow disturbances caused a modulation of the unsteady disturbances, resulting in spatially concentrated peaks in unsteady disturbance amplitude. This modulation of the unsteady disturbances is believed to be the reason for the upstream movement of the transition front with increasing stationary crossflow amplitude.

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          Most cited references25

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          Boundary-Layer Transition

          I Tani (1969)
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            Effect of surface steps on boundary layer transition

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              Effect of Isolated Micron-Sized Roughness on Transition in Swept-Wing Flows

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                Author and article information

                Conference
                aiaaj
                AIAA Journal
                AIAA Journal
                American Institute of Aeronautics and Astronautics
                0001-1452
                1533-385X
                14 September 2017
                February 2018
                : 56
                : 2
                : 497-509
                Affiliations
                NASA Langley Research Center, Hampton, Virginia 23681
                Iowa State University , Ames, Iowa 50011
                NASA Langley Research Center, Hampton, Virginia 23681
                Author notes
                [*]

                Research Aerospace Engineer, Flow Physics and Control Branch, M.S. 170. Member AIAA.

                [†]

                Professor and Vance and Arlene Coffman Endowed Department Chair in Aerospace Engineering, 2271 Howe Hall, Room 1200A. Fellow AIAA.

                [‡]

                Research Aerospace Engineer, Computational Aerosciences Branch, M.S. 128. Associate Fellow AIAA.

                Article
                J056267 J056267
                10.2514/1.J056267
                bdee7c17-cd46-4fc5-b19a-3678f439660d
                This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0001-1452 (print) or 1533-385X (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 1 May 2017
                : 4 August 2017
                : 6 August 2017
                Page count
                Figures: 18, Tables: 1
                Categories
                Regular Article

                Engineering,Physics,Mechanical engineering,Space Physics
                Engineering, Physics, Mechanical engineering, Space Physics

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