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Acta Aeronautica et Astronautica Sinica ›› 2023, Vol. 44 ›› Issue (18): 28411-028411.doi: 10.7527/S1000-6893.2023.28411

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Research progress of shock wave/boundary layer interaction controls induced by bump

Shanshan TIAN1,2, Liang JIN1, Zhaobo DU1, Xiangyu ZHONG1, Wei HUANG1(), Yuanyang LIU2   

  1. 1.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China
    2.31672 Troop of the People’s Liberation Army of China,Shenzhen 518000,China
  • Received:2022-12-19 Revised:2023-01-10 Accepted:2023-02-06 Online:2023-09-25 Published:2023-02-10
  • Contact: Wei HUANG E-mail:gladrain2001@163.com
  • Supported by:
    National Key R & D Program of China(2019YFA0405300);National Natural Science Foundation of China(11972368)

Abstract:

The flow control of hypersonic vehicles faces complex shock wave/boundary layer interaction problems, and effective shock wave/boundary layer interaction control technologies have become a research hotspot. This paper reviews the research progress of passive control of shock wave/boundary layer interaction based on bumps. The main flow characteristics of shock wave/boundary layer interaction are introduced, and the research progress of shock wave/boundary layer interaction is summarized. The mechanism and research progress of shock wave control bumps for drag reduction of transonic wings in the external flow field, and wall bumps for supersonic and hypersonic flow control in the internal flow field are reviewed. The flow control performance of bumps is analyzed and its development prospected.

Key words: shock wave/boundary layer interaction, flow separation, flow control, bump, passive control

CLC Number: