| 涡升力乘波体发展研究综述 |
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| 引用本文： | 易怀喜,王逗,李珺,罗世彬. 涡升力乘波体发展研究综述[J]. 航空工程进展, 2021, 12(6): 1-12 |
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| 作者姓名： | 易怀喜 王逗 李珺 罗世彬 |
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| 作者单位： | 中南大学 航空航天学院,长沙 410083 |
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| 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。
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| 关 键 词： | 涡升力乘波体 涡效应 激波效应 宽速域 |
| 收稿时间： | 2020-08-31 |
| 修稿时间： | 2021-06-20 |
Overview on the development research of vortex lift waverider |
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| YI Huaixi,WANG Dou,LI Jun and LUO Shibin. Overview on the development research of vortex lift waverider[J]. Advances in Aeronautical Science and Engineering, 2021, 12(6): 1-12 |
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| Authors: | YI Huaixi WANG Dou LI Jun LUO Shibin |
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| Affiliation: | School of Aeronautics and Astronautics,Central South University,School of Aeronautics and Astronautics,Central South University,School of Aeronautics and Astronautics,Central South University,School of Aeronautics and Astronautics,Central South University |
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| Abstract: | In order to maintain good aerodynamic performance in both low and hypersonic velocity, related scholars took the advantages of the planform-controllable waverider and proposed the "vortex lift" waverider. This paper summarized 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 method based on the shock-fitting method, and the projection method based on the given shock surface. The relevant research on the aerodynamic characteristics of the vortex lift waverider in the wide speed range was also reviewed, and some suggestions are put forward to the following research of vortex lift waveriders. |
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| Keywords: | Vortex lift waverider Vortex effect Shock wave effect Width-velocity range |
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