基于鼓包的激波/边界层干扰控制研究进展  

Research progress of shock wave/boundary layer interaction controls induced by bump

作　　者：田珊珊 金亮[1] 杜兆波 钟翔宇 黄伟[1] 刘远洋 TIAN Shanshan;JIN Liang;DU Zhaobo;ZHONG Xiangyu;HUANG Wei;LIU Yuanyang(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;31672 Troop of the People’s Liberation Army of China,Shenzhen 518000,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]中国人民解放军31627部队,深圳518000

出　　处：《航空学报》2023年第18期32-55,共24页Acta Aeronautica et Astronautica Sinica

基　　金：国家重点研发计划(2019YFA0405300);国家自然科学基金(11972368)。

摘　　要：超声速及高超声速飞行器在飞行过程中存在复杂的激波/边界层干扰问题,有效的流动控制技术已成为研究热点,鼓包是一项具有发展前景的被动控制技术。本文基于鼓包的控制机理,对激波/边界层干扰的被动控制技术研究进展进行了综述。介绍了激波/边界层干扰的主要流动特征并总结归纳了其研究现状;总结了常见的流动控制方法,分别对外流场中跨声速机翼减阻的激波控制鼓包、内流场中超声速及高超声速流动控制的壁面鼓包的作用机理及其研究进展进行了梳理,分析了鼓包的流动控制性能并对其发展前景进行了展望。The flow control of hypersonic vehicles faces complex shock wave/boundary layer interaction problems,and effective shock wave/boundary layer interaction control technologies have become a research hotspot.This paper reviews the research progress of passive control of shock wave/boundary layer interaction based on bumps.The main flow characteristics of shock wave/boundary layer interaction are introduced,and the research progress of shock wave/boundary layer interaction is summarized.The mechanism and research progress of shock wave control bumps for drag reduction of transonic wings in the external flow field,and wall bumps for supersonic and hypersonic flow control in the internal flow field are reviewed.The flow control performance of bumps is analyzed and its development prospected.

关 键 词：激波/边界层干扰 流动分离 流动控制 鼓包 被动控制 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]