| 二元混压式高超声速进气道流场数值模拟 |
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| 引用本文： | 王雨培,于澎,宋文艳.二元混压式高超声速进气道流场数值模拟[J].现代防御技术,2006,34(6):44-47. |
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| 作者姓名： | 王雨培 于澎 宋文艳 |
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| 作者单位： | 1. 中国航天科工集团公司,二院二部,北京,100854
2. 西北工业大学,陕西,西安,710072 |
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| 摘 要： | 使用有限差分法,TVD二阶迎风格式,Baldwin-Lomax湍流模型,对二元混压式高超声速进气道设计状态和非设计状态的粘性流场和性能进行了数值模拟,并分析了出口反压及隔离段长度对进气道流场的影响。结果表明隔离段长高比对进气道出口参数影响较大;隔离段出口反压不能太高,否则会引起进气道不起动。
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| 关 键 词： | 超燃冲压发动机 高超声速进气道 隔离段 数值模拟 |
| 文章编号： | 1009-086X(2006)-06-0044-04 |
| 修稿时间： | 2006年1月3日 |
Numerical simulations of hypersonic inlet flowfields in the binary mixed compression |
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| WANG Yu-pei,YU Peng,SONG Wen-yan.Numerical simulations of hypersonic inlet flowfields in the binary mixed compression[J].Modern Defence Technology,2006,34(6):44-47. |
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| Authors: | WANG Yu-pei YU Peng SONG Wen-yan |
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| Abstract: | The hypersonic inlet viscous flow field in design and off-design condition is simulated by using finite difference method,TVD(2nd) order upwind scheme and Baldwin-Lomax turbulence model.The flow equations are solved by a local time-stepping approach.Then the effect of back pressure and the length of isolator on inlet flow fields are analyzed.The results show the exit back pressure and length/height ratio of isolator have great impact on exit flow field and starting performance of inlet,that is,high back pressure of inlet will result in unstart. |
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| Keywords: | scramjet hypersonic inlet isolator numerical simulation |
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