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Research progress of flow control on shock wave/boundary layer interaction in supersonic inlets
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Yunkai WU1, Xiaogang MA1, Liming FENG2, Xiwei CAO3, Jian FAN3, Rui XUE1
Chinese Journal of Applied Mechanics | 2025, 42(6) : 1207 - 1223
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Chinese Journal of Applied Mechanics | 2025, 42(6): 1207-1223
• Experts’ Review •
Research progress of flow control on shock wave/boundary layer interaction in supersonic inlets
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Yunkai WU1, Xiaogang MA1, Liming FENG2, Xiwei CAO3, Jian FAN3, Rui XUE1
Affiliations
  • 1.State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace Engineering, Xi'an Jiaotong University, 710049 Xi'an, China
  • 2.China Aerodynamic Research and Development Center, 621000 Mianyang, China
  • 3.Beijing Institute of Astronautical Systems Engineering, 100076 Beijing, China
Published: 2025-12-15 doi: 10.11776/j.issn.1000-4939.2025.06.001
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There are complex flow phenomena in the inlets of the air-breathing hypersonic vehicles, such as boundary layer transition, flow separation, and shock/boundary layer interference. Deep understanding and effective control of these complex flow phenomena are the key to realizing effective operation and performance improvement of hypersonic vehicles. The current research progress of shock/boundary layer flow control technology in supersonic inlets is first reviewed from two aspects:passive control and active control；their effectiveness and drawbacks are described. Meanwhile, with the development of hypersonic vehicle towards the direction of wide velocity domain, large airspace and high Mach number, the previous flow control technology based on active and passive control cannot meet the requirements of hypersonic vehicle follow-up control. As a result, the multi-field control methods represented by plasma have become the focus of supersonic inlets flow control. However, the existing experimental research methods are difficult to carry out detailed research on flow control mechanisms, and there are still many places worth exploring. In this paper, relevant suggestions are put forward for the next step of research in addition to summarizing.

hypersonic  /  flow control  /  plasma  /  shock wave/boundary layer interaction
Yunkai WU, Xiaogang MA, Liming FENG, Xiwei CAO, Jian FAN, Rui XUE. Research progress of flow control on shock wave/boundary layer interaction in supersonic inlets[J]. Chinese Journal of Applied Mechanics, 2025 , 42 (6) : 1207 -1223 . DOI: 10.11776/j.issn.1000-4939.2025.06.001
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Article Info
doi: 10.11776/j.issn.1000-4939.2025.06.001
  • Receive Date：2024-03-19
  • Online Date：2026-03-27
  • Published：2025-12-15
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  • Received：2024-03-19
Funding
Affiliations
    1.State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace Engineering, Xi'an Jiaotong University, 710049 Xi'an, China
    2.China Aerodynamic Research and Development Center, 621000 Mianyang, China
    3.Beijing Institute of Astronautical Systems Engineering, 100076 Beijing, China
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https://castjournals.cast.org.cn/joweb/yylxxb/EN/10.11776/j.issn.1000-4939.2025.06.001
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