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      Effect of Two-Dimensional Short Rectangular Indentations on Hypersonic Boundary-Layer Transition

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          Abstract

          The objective of the present paper is to reveal the intrinsic mechanisms by which two-dimensional surface indentations influence the laminar–turbulent transition of natural route in hypersonic boundary layers. For an oncoming Mach number of 6 and a rectangular indentation, two relevant scattering mechanisms, namely, the local scattering of oncoming Mack modes and the local receptivity to freestream acoustic waves, are studied by direct numerical simulations. A transmission coefficient and a receptivity coefficient are introduced to quantify the two mechanisms, and their dependence on the indentation depths and the oncoming-perturbation frequencies is investigated systematically. Numerical results reveal that both the local scattering and receptivity effects increase with the indentation depth when the latter is shallow, but the opposite is true for deep indentations. Such a phenomenon is found to be related to the topological structure of the base flow inside the indentations, namely, two independent separation bubbles for shallow configurations and one large-scale separation bubble occupying the whole indentation for deep configurations.

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          Most cited references45

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          Efficient Implementation of Weighted ENO Schemes

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            Physical Mechanisms of Laminar-Boundary-Layer Transition

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              Transition and Stability of High-Speed Boundary Layers

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                Author and article information

                Contributors
                Journal
                aiaaj
                AIAA Journal
                AIAA Journal
                American Institute of Aeronautics and Astronautics
                1533-385X
                22 March 2021
                July 2021
                : 59
                : 7
                : 2368-2381
                Affiliations
                Tianjin University , Tianjin 300072, People’s Republic of China
                Author notes
                [*]

                Associate Professor, Department of Mechanics, 92 Weijin Road, Nankai District; dongming@ 123456tju.edu.cn .

                [†]

                Master Student, Department of Mechanics, 92 Weijin Road, Nankai District.

                Author information
                https://orcid.org/0000-0003-3408-8613
                Article
                J059957 J059957
                10.2514/1.J059957
                2cb1bb0f-dfb0-468a-8ab6-8314b0e27779
                Copyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 05 July 2020
                : 29 November 2020
                : 10 December 2020
                Page count
                Figures: 22, Tables: 2
                Funding
                Funded by: National Natural Science Foundation of Chinahttp://dx.doi.org/10.13039/501100001809
                Award ID: U20B2003
                Award ID: 11772224
                Award ID: 91952202
                Categories
                Regular Articles
                p2263, Fluid Dynamics
                p1975, Boundary Layers
                p1976, Flow Regimes
                p3282, Computational Fluid Dynamics
                p1804, Aerodynamics
                p3278, Fluid Flow Properties
                p2057, Finite Element Method
                p1973, Vortex Dynamics
                p16591, Finite Difference Method
                p20543, Aerodynamic Performance

                Engineering,Physics,Mechanical engineering,Space Physics
                Angle of Attack,Mach Number,Kinematic Viscosity,Direct Numerical Simulation,Compressible Flow,Laminar Turbulent Transition,Kinetic Energy,Finite Difference Scheme,Vortex Shedding,Shape Functions

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