| 马赫数4～7的高超侧压式进气道气动设计与性能 |
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| 引用本文： | 金志光,张堃元,刘媛.马赫数4～7的高超侧压式进气道气动设计与性能[J].航空动力学报,2011,26(6):1201-1208. |
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| 作者姓名： | 金志光 张堃元 刘媛 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
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| 基金项目： | 南京航空航天大学青年科技创新基金(NS2010039) |
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| 摘 要： | 对巡航马赫数为7、转级马赫数为4的宽范围侧压式进气道进行了设计,讨论了主要设计参数的选取原则,给出了一种曲面压缩的高性能侧压式进气道设计方案,并利用数值仿真手段对其流场结构及性能进行了研究.结果表明,所设计的侧压式进气道在马赫数Ma=4时的流量系数达到0.753,最大正攻角可达6°以上.Ma=6时,流量系数达到0.94...
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| 关 键 词： | 超燃冲压发动机进气道 侧压式进气道 曲面压缩 攻角特性 侧滑角特性 数值仿真 |
| 收稿时间： | 2010/5/13 0:00:00 |
| 修稿时间： | 2010/12/14 0:00:00 |
Design and performance investigation of sidewall compression scramjet inlets operating from Mach 4 to Mach 7 |
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| JIN Zhi-guang,ZHANG Kun-yuan and LIU Yuan.Design and performance investigation of sidewall compression scramjet inlets operating from Mach 4 to Mach 7[J].Journal of Aerospace Power,2011,26(6):1201-1208. |
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| Authors: | JIN Zhi-guang ZHANG Kun-yuan and LIU Yuan |
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| Institution: | JIN Zhi-guang,ZHANG Kun-yuan,LIU Yuan(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China) |
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| Abstract: | Three-dimensional sidewall compression scramjet inlets with fore body compression operating in a large Mach number range from 4 to 7 were designed.The selection principles of the inlet primary design parameters were discussed and a high performance inlet scheme with curved surface compression was given.The complex flow field structure and the global performance of the scramjet inlet were investigated by means of numerical simulations.Results indicate at Mach 4 starting point,the sidewall compression scramje... |
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| Keywords: | scramjet inlet sidewall compression scramjet inlet curved surface compression characteristic of attack angle characteristic of yaw angle numerical simulation |
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