Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators
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Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering) ISSN 1673-565X (Print); ISSN 1862-1775 (Online) www.jzus.zju.edu.cn; www.springerlink.com E-mail: [email protected]
Hypersonic flow control of shock wave/turbulent boundary layer interactions using magnetohydrodynamic plasma actuators* Hao JIANG†, Jun LIU, Shi-chao LUO, Jun-yuan WANG, Wei HUANG Science and Technology on Scramjet Laboratory, National University of Defense Technology, Changsha 410073, China †
E-mail: [email protected]
Received Jan. 17, 2020; Revision accepted June 5, 2020; Crosschecked Aug. 28, 2020
Abstract: The effect of magnetohydrodynamic (MHD) plasma actuators on the control of hypersonic shock wave/turbulent boundary layer interactions is investigated here using Reynolds-averaged Navier-Stokes calculations with low magnetic Reynolds number approximation. A Mach 5 oblique shock/turbulent boundary layer interaction was adopted as the basic configuration in this numerical study in order to assess the effects of flow control using different combinations of magnetic field and plasma. Results show that just the thermal effect of plasma under experimental actuator parameters has no significant impact on the flow field and can therefore be neglected. On the basis of the relative position of control area and separation point, MHD control can be divided into four types and so effects and mechanisms might be different. Amongst these, D-type control leads to the largest reduction in separation length using magnetically-accelerated plasma inside an isobaric dead-air region. A novel parameter for predicting the shock wave/turbulent boundary layer interaction control based on Lorentz force acceleration is then proposed and the controllability of MHD plasma actuators under different MHD interaction parameters is studied. The results of this study will be insightful for the further design of MHD control in hypersonic vehicle inlets. Key words: Hypersonic; Shock wave/turbulent boundary layer interaction; Magnetohydrodynamic (MHD); Flow control https://doi.org/10.1631/jzus.A2000025 CLC number: V211.48
1 Introduction As hypersonic vehicles become able to reach higher Mach numbers (Ma) in the relatively lower layers of near space, the shock wave/turbulent boundary layer interaction (STBLI) of internal and external aerodynamics become more obvious (Zhang et al., 2019; Huang et al., 2020). Oblique STBLI is a typical configuration for the intake of hypersonic vehicles; this means that the strong adverse pressure gradient brought about by the compression wave system of intake causes the boundary layer to separate and generate complex and unsteady wave systems. *
Project supported by the National Key R&D Program of China (Nos. 2019YFA0405300 and 2019YFA0405203) and the Chinese Scholarship Council (CSC) (No. 201903170195) ORCID: Hao JIANG, https://orcid.org/0000-0001-7251-7875 © Zhejiang University and Springer-Verlag GmbH Germany, part of Springer Nature 2020
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