涡升力乘波体发展研究综述  

Overview on the Development Research of Vortex Lift Waverider

作　　者：易怀喜 王逗 李珺 罗世彬 YI Huaixi;WANG Dou;LI Jun;LUO Shibin(School of Aeronautics and Astronautics,Central South University,Changsha 410083,China)

机构地区：[1]中南大学航空航天学院,长沙410083

出　　处：《航空工程进展》2021年第6期1-12,共12页Advances in Aeronautical Science and Engineering

摘　　要：乘波飞行器在高超声速具有良好的气动性能,但偏离设计状态,气动性能则难以保持。为在宽速域范围能一直维持较好的气动性能,研究人员利用定平面形状乘波设计的优势,提出“涡升力”乘波设计。本文将涡升力乘波体的设计方法归纳为基于吻切理论的定前缘型线法、基于激波装配法的波导体法和基于给定激波面的投影法三大类,综述了涡升力乘波体在宽速域气动特性的相关研究进展,并对涡升力乘波体的后续研究提出建议。The waverider has good aerodynamic performance in hypersonic flight,however its performance is diffi⁃cult to maintain when it deviates from the design state.In order to maintain good aerodynamic performance in both low and hypersonic velocity,related researchers took the advantages of the planform-controllable waverider and put forward the“vortex lift”waverider.In this paper,the three types of vortex lift waveriders design method,namely the fixed leading edge profile method based on the osculating cone theory,the shock generating body meth⁃od based on the shock-fitting method,and the projection method based on the given shock surface are summarized.The relevant research on the aerodynamic characteristics of the vortex lift waverider in the wide speed range is also reviewed,and some suggestions are put forward to the following research of vortex lift waveriders.

关 键 词：涡升力乘波体 涡效应 激波效应 宽速域 

分 类 号：V211.5[航空宇航科学与技术—航空宇航推进理论与工程]