Review of researches on compressible turbulent boundary layer combustion for skin friction reduction

LIU Hongpeng; GAO Zhenxun; JIANG Chongwen; LEE Chunhian

doi:10.7638/kqdlxxb-2019.0147

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Review of researches on compressible turbulent boundary layer combustion for skin friction reduction

更新时间：2026-05-28

- Review of researches on compressible turbulent boundary layer combustion for skin friction reduction
- Vol. 38, Issue 3, Pages: 593-602(2020)
- 作者机构：
  
  北京航空航天大学航空科学与工程学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0147
  CLC： V211.3;TK16
- Published：2020
- 稿件说明：
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刘宏鹏, 高振勋, 蒋崇文, 李椿萱. 可压缩湍流边界层燃烧减阻研究综述[J]. 空气动力学学报, 2020, 38(3): 593-602.

LIU Hongpeng, GAO Zhenxun, JIANG Chongwen, et al. Review of researches on compressible turbulent boundary layer combustion for skin friction reduction[J]. 2020, 38(3): 593-602.
刘宏鹏, 高振勋, 蒋崇文, 李椿萱. 可压缩湍流边界层燃烧减阻研究综述[J]. 空气动力学学报, 2020, 38(3): 593-602. DOI： 10.7638/kqdlxxb-2019.0147.

LIU Hongpeng, GAO Zhenxun, JIANG Chongwen, et al. Review of researches on compressible turbulent boundary layer combustion for skin friction reduction[J]. 2020, 38(3): 593-602. DOI： 10.7638/kqdlxxb-2019.0147.

摘要

减阻设计对于提高超燃冲压发动机性能具有重要意义，而边界层燃烧是一种有效的减阻方法。综述分别从实验、理论和数值模拟研究方面介绍了边界层燃烧减阻的相关进展。实验研究验证了边界层燃烧减阻的有效性，研究了不同因素对边界层燃烧减阻效率的影响，初步形成了将该减阻技术应用于高超声速飞行器的能力。理论研究建立了考虑边界层燃烧的壁面摩阻、热流理论计算模型，而数值模拟帮助揭示了边界层燃烧减阻的内在物理机理。澳大利亚Queensland大学在该方面开展了较为系统的研究，欧洲、美国、俄罗斯、日本等在该方面极少公开发表相关研究成果。中国学者取得了一定进展，但与世界先进水平仍有较大差距，尤其是在实验研究方面。

Abstract

Drag reduction is important for improving the performance of scramjet engines operating at high Mach numbers. One demonstrated method for reducing skin friction drag on a surface exposed to hypersonic flow is the injection and combustion of hydrogen fuel in the boundary layer. This paper reviews the research progresses of skin friction reduction by boundary layer combustion from three aspects including experiments

theory analyses

and numerical simulations. The experiments have demonstrated their effectiveness and analyzed different influencing factors. The ability of applying this drag reduction technique to real hypersonic flight vehicles is primarily established. The theoretical prediction model for skin friction and heat flux of the boundary layer flow where the combustion occurs has been proposed and its accuracy was demonstrated by comparing with experiments and numerical studies. The numerical simulations have helped researchers to understand the mechanism of skin friction reduction by boundary layer combustion deeply. For the research progresses of this technique

University of Queensland in Australia is at the leading level of the world. Europe

America

Russia and Japan seem having little interest on this field and very few technical papers can be found publicly from these countries. While Chinese researchers has made some progresses but still need to do lots of work

epspcially in the experimental field

to catch up with the world leading level.

关键词

Keywords

references

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