航空学报 > 2021, Vol. 42 Issue (6): 25371-025371   doi: 10.7527/S1000-6893.2021.25371

激波/边界层干扰及微型涡流发生器控制研究进展

吴瀚, 王建宏, 黄伟, 杜兆波, 颜力   

  1. 国防科技大学 空天科学学院, 长沙 410073
  • 收稿日期:2021-02-04 修回日期:2021-02-22 发布日期:2021-03-18
  • 通讯作者: 黄伟 E-mail:gladrain2001@163.com
  • 基金资助:
    国家重点研发计划(2019YFA0405300)

Research progress on shock wave/boundary layer interactions and flow controls induced by micro vortex generators

WU Han, WANG Jianhong, HUANG Wei, DU Zhaobo, YAN Li   

  1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
  • Received:2021-02-04 Revised:2021-02-22 Published:2021-03-18
  • Supported by:
    National Key R&D Program of China (2019YFA0405300)

摘要: 激波/边界层干扰是一种发生在超声速/高超声速流动中的普遍现象。该现象将引起分离、流场结构振荡、局部高热通量和压力载荷。主要总结了近十年来激波/边界层干扰特性与微型涡流发生器及其组合体在流动控制中的最新进展。微型涡流发生器是目前研究最多、应用最广泛的控制方法,其流动机理和控制特性被大量挖掘。为了适应来流条件的变化、满足实际工况的需要,应开发定量评估和参数化设计方法。同时,应探索微型涡流发生器与其他控制方法的组合,实现更大程度、更广范围流场的控制。

关键词: 激波/边界层干扰, 超声速/高超声速流动, 流动分离, 流动控制, 微型涡流发生器

Abstract: The shock wave/boundary layer interaction is a common phenomenon that occurs in supersonic/hypersonic flows, causing flow separation, flow field structure oscillation, local high heat flux and pressure load. This article mainly summarizes recent research advances on the shock wave/boundary layer interaction and its control induced by the micro vortex generator in the past decade. The micro vortex generator is currently the most studied and widely used control approach with its flow performance and control mechanism extensively explored. However, to adapt to the changes in incoming flow conditions and meet the needs of actual working conditions, quantitative evaluation and parametric design methods should be developed. Meanwhile, the combination of the micro vortex generator and other control methods should be considered to achieve flow field control with a larger degree and a wider range.

Key words: shock wave/boundary layer interaction, supersonic/hypersonic flow, flow separation, flow control, micro vortex generators

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