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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (1): 625929-625929.doi: 10.7527/S1000-6893.2021.25929

• Special Topic of Shock/Boundary Layer Interation Mechanism and Control • Previous Articles     Next Articles

Flow control technique for shock wave/turbulent boundary layer interactions

SHI Xiaotian, LYU Meng, ZHAO Yuan, TAO Shancong, HAO Le, YUAN Xiangjiang   

  1. China Academy of Aerospace Aerodynamics, Beijing 100074, China
  • Received:2021-06-07 Revised:2021-09-23 Online:2022-01-15 Published:2021-09-22
  • Supported by:
    National Key R&D Program of China(2019YFA0405300); National Natural Science Foundation of China(11872348, 11802297)

Abstract: 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.

Key words: shock wave/turbulent boundary layer interaction, flow control, flow separation, vortex generator, plasma actuator

CLC Number: