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激波/湍流边界层干扰的流动控制技术(高超边界层专栏)

时晓天,袁湘江   

  1. 中国航天空气动力技术研究院
  • 收稿日期:2021-06-07 修回日期:2021-09-13 出版日期:2021-09-22 发布日期:2021-09-22
  • 通讯作者: 袁湘江
  • 基金资助:
    国家重点研发计划,科技部大科学装置前沿技术研究;高超声速边界层基于流动结构的降热减阻流动控制技术

Flow Control Method for Shock/Turbulent Boundary Layer Interactions

Xiaotian -Shi,   

  • Received:2021-06-07 Revised:2021-09-13 Online:2021-09-22 Published:2021-09-22

摘要: 激波/湍流边界层干扰是航空航天领域中广泛存在的一种复杂流动现象,形成条件涵盖跨声速到高超声速,形成环境复杂多样,给飞行器的气动和结构设计带来严重的影响。为提高激波/湍流边界层的流动控制能力,更好的为工程应用服务,本文系统的梳理了激波/湍流边界层研究过程中的重要研究发现和研究进展;总结了应用于激波/湍流边界层流动的代表性流动控制技术,如涡发生器、电磁激励、射流、非定常抽吸气、多孔壁面、鼓包等主被动流动控制技术的控制原理、能力、现状及不足;最后探讨了激波/湍流边界层干扰流动控制有待于进一步深入研究的问题,旨在形成激波/边界层干扰流动控制能力的系统认识,为该问题尤其是高超声速条件下的流动控制形成解决方案和技术储备。

关键词: 激波/湍流边界层干扰, 流动控制, 流动分离, 涡发生器, 等离子体

Abstract: Shock/turbulent boundary layer interaction(STBLI) is ubiquitous presence in aircraft engineering, occurring in the case from transonic to hypersonic, complex linear and nonlinear mechanisms are involved. Flow separation, peak heating and low frequency pressure fluctuating in strong interactions can effect vehicle, inlet and component geometry, structural integrity, material selection, fatigue life and the design of thermal protection systems. Flow control is viewed by many as a key issue to adjust the flow field of STBLI. Flow control technique such as vortex generator, plasma and MHD, steady and pulse jet, perforated surface and bump are utilized for STBLI control to improve the performance of aircraft. In the present paper, a comprehensive review on the important knowledge, most of the flow control technique for STBLI are summarized to deepen the understanding of STBLI and its flow control, for improving the flow control design and troubleshooting of STBLI in engineering, espacially in the case of hypersonic

Key words: shock/turbulent boundary layer interaction(STBLI), flow control, flow separation, vortex generator, plasma