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延迟高超声速边界层转捩技术研究进展

发布日期: 2022-09-30 | 浏览次数: 182

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    

Progress in hypersonic boundary layer transition delay control

LIU Qiang1,2, TU Guohua1, LUO Zhenbing2, CHEN Jianqiang1, ZHAO Rui3, YUAN Xianxu1    


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


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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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