Flow control technique for shock wave/turbulent boundary layer interactions

被引：0
作者：
Shi X. [1 ]
Lyu M. [1 ]
Zhao Y. [1 ]
Tao S. [1 ]
Hao L. [1 ]
Yuan X. [1 ]
机构：
[1] China Academy of Aerospace Aerodynamics, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 01期
基金：
中国国家自然科学基金;
关键词：
Flow control; Flow separation; Plasma actuator; Shock wave/turbulent boundary layer interaction; Vortex generator;
D O I：
10.7527/S1000-6893.2021.25929
中图分类号：
学科分类号：
摘要：
Shock wave/Turbulent Boundary Layer Interaction(STBLI) is ubiquitous presence in aircraft engineering. Occurring in the case from transonic to hypersonic, the complex linear and nonlinear mechanisms in the STBLI such as the flow separation, peak heating and low frequency pressure fluctuating can heavily affect the vehicle, inlet and component geometry, structural integrity, material selection, fatigue life and the design of thermal protection systems. Therefore, the flow control is considered as a key issue to adjust the flow field of STBLI. To deepen the understanding of STBLI and its flow control, the present paper conducted a comprehensive review on the important knowledge, mostly the flow control techniques such as vortex generator, plasma and magnetohydrodynamics for STBLI to improve the flow control design and troubleshooting of STBLI in engineering, especially in the case of hypersonic. © 2022, Beihang University Aerospace Knowledge Press. All right reserved.
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