摘要
激波/边界层干扰现象在超声速流场中不可避免,这种现象的存在会对超声速飞行器内外流场产生一系列的不利影响。所以,对激波/边界层干扰现象进行控制是十分必要的。微射流主动流动控制方法近年来已成为流动控制领域的研究热点。本文梳理了近年来微射流主动流动控制方法对激波/边界层干扰控制的相关研究进展,综合分析了影响单孔微射流和微射流阵列控制效果的因素,并对目前研究的不足和发展前景进行了探讨,以期对相关研究提供参考。
The phenomenon of shock wave/boundary layer interaction is inevitable in the supersonic flow field.The existence of this phenomenon will have a series of adverse effects on the inner and outer flow fields of the supersonic vehicle.Therefore,it is necessary to control the shock wave/boundary layer interaction.Microjet active flow control method has become a research hotspot in the field of flow control in recent years.This paper summarizes the latest research progress of microjet active flow control method in the control of shock/boundary layer interaction,comprehensively analyzes the factors affecting the control effect of single-hole microjet and microjet arrays.In addition,it discusses the shortcomings and development prospects of current research.This paper can provide some references for related research.
作者
徐浩
杜兆波
钟翔宇
黄伟
Xu Hao;Du Zhaobo;Zhong Xiangyu;Huang Wei(College of Aerospace Science,National University of Defense Technology,Changsha 410073,China)
出处
《航空兵器》
CSCD
北大核心
2022年第4期83-90,共8页
Aero Weaponry
基金
国家自然科学基金项目(11972368)
国家重点研发计划(2019YFA0405300)。
关键词
激波/边界层干扰
流动分离
微射流
流动控制
涡对
流场
超声速飞行器
shock wave/boundary layer interactions
flow separation
microjet
flow control
vortex pair
flow field
supersonic vehicle
