延迟高超声速边界层转捩技术研究进展

doi:10.7527/S1000-6893.2021.25357

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延迟高超声速边界层转捩技术研究进展

刘强^1,2, 涂国华¹, 罗振兵², 陈坚强¹, 赵瑞³, 袁先旭¹

1. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000;
2. 国防科技大学空天科学学院, 长沙 410073;
3. 北京理工大学宇航学院, 北京 100081

收稿日期:2021-02-04 修回日期:2021-04-09 出版日期:2022-07-15 发布日期:2021-04-08
通讯作者: 涂国华,E-mail:ghtu@skla.cardc.cn E-mail:ghtu@skla.cardc.cn
基金资助:
国家自然科学基金(11772350,92052301,11872374,11872116);国家重点研发计划(2016YFA0401200)

Progress in hypersonic boundary layer transition delay control

LIU Qiang^1,2, TU Guohua¹, LUO Zhenbing², CHEN Jianqiang¹, ZHAO Rui³, YUAN Xianxu¹

1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China;
3. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received:2021-02-04 Revised:2021-04-09 Online:2022-07-15 Published:2021-04-08
Supported by:
National Natural Science Foundation of China (11772350, 92052301, 11872374, 11872116); National Key R & D Program of China (2016YFA0401200)

摘要/Abstract

摘要： 由于高超声速情况下边界层从层流转捩成湍流后,壁面摩阻和热流出现数倍增长,控制高超声速边界层使转捩延迟对飞行器减阻降热具有十分重要的意义。首先,概述了高超声速边界层的主要失稳机制;其次,从被动控制技术和主动控制技术两个角度回顾了当前高超声速边界层转捩延迟控制技术的最新进展,先详细介绍了粗糙元、波纹壁和微孔隙壁面等被动控制方法,然后详细介绍了壁面加热/冷却、重气体喷注等主动控制方法,分析了控制背后的物理机制,讨论了各种控制技术的优缺点;最后,对转捩延迟控制技术的进一步研究给出了建议和展望。

关键词: 高超声速飞行器, 边界层转捩, 转捩延迟, 流动控制, 降热减阻

Abstract: Due to the large difference between laminar flow and turbulent flow in wall friction and wall heat flow, the transition control of the hypersonic boundary layer is of vital importance to the aerodynamic performance and thermal protection system of vehicles. This paper first summarizes the main instability mechanisms of hypersonic boundary layers, followed by a review of the latest progress in the hypersonic boundary layer transition delay control technology from two aspects, namely, passive control and active control technologies. Passive control methods such as roughness elements, wavy wall, and porous coating are then introduced in detail, the active control measures such as wall heating/cooling and heavy gas injection described, the physical mechanism behind the control analyzed, and the advantages and disadvantages of various control technologies discussed. Finally, suggestions and prospects for further research on transition delay control are presented.

Key words: hypersonic flight vehicles, boundary layer transition, transition delay, flow control, drag and heat reductionhttp

中图分类号:

V211

刘强, 涂国华, 罗振兵, 陈坚强, 赵瑞, 袁先旭. 延迟高超声速边界层转捩技术研究进展[J]. 航空学报, 2022, 43(7): 25357-025357.

LIU Qiang, TU Guohua, LUO Zhenbing, CHEN Jianqiang, ZHAO Rui, YUAN Xianxu. Progress in hypersonic boundary layer transition delay control[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(7): 25357-025357.

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延迟高超声速边界层转捩技术研究进展

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