| 高超声速飞行器后体喷管三维构型设计 |
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| 引用本文： | 徐大军,陈兵,蔡国飙,徐旭. 高超声速飞行器后体喷管三维构型设计[J]. 航空动力学报, 2009, 24(2): 247-254 |
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| 作者姓名： | 徐大军 陈兵 蔡国飙 徐旭 |
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| 作者单位： | 北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191;北京航空航天大学宇航学院,北京,100191 |
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| 摘 要： | 为研究高超声速飞行器后体喷管三维构型的设计,以NASA半壁喷管试验为参考,进行了二维及三维内外流相互作用的数值模拟计算,分析了后体喷管三维流场的特点.从高超声速飞行器机身推进一体化的角度,构建了后体喷管三维构型,进行了不同构型设计对后体喷管性能影响的参数研究.结果表明:后体喷管的三维效应不可忽视,后体喷管侧壁的存在及下壁面长度对性能影响较大.
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| 关 键 词： | 高超声速飞行器 一体化设计 后体喷管 三维构型 数值模拟 |
| 收稿时间： | 2008-01-22 |
| 修稿时间： | 2008-06-02 |
Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle |
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| XU Da-jun,CHEN Bing,CAI Guo-biao and XU Xu. Design of three dimensional afterbody/nozzle configuration of airbreathing hypersonic vehicle[J]. Journal of Aerospace Power, 2009, 24(2): 247-254 |
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| Authors: | XU Da-jun CHEN Bing CAI Guo-biao XU Xu |
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| Affiliation: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Three dimensional configuration design of afterbody/nozzle was studied in this paper.Flow filed numerical simulations were conducted on NASA single expansion ramp nozzle experiment model.Numerical simulation results of two-dimensional and three-dimensional flow field without/with side fence were compared with experiment data and structure of three-dimensional flow filed.From the viewpoint of hypersonic vehicle airframe/propulsion integrated design,three-dimensional configuration of afterbody/nozzle was cons... |
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| Keywords: | hypersonic vehicle integrated design afterbody/nozzle three-dimensional configuration numerical simulation |
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