| 二维高超声速进气道优化设计方法研究 |
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| 引用本文： | 王向转,詹浩,朱军.二维高超声速进气道优化设计方法研究[J].飞行力学,2009,27(4). |
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| 作者姓名： | 王向转 詹浩 朱军 |
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| 作者单位： | 西北工业大学,航空学院,陕西,西安,710072 |
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| 摘 要： | 对二维高超声速进气道的优化设计方法进行了研究。采用拟Newton法作为优化方法,结合代数法生成的结构化网格以及流体计算软件Fluent,形成对二维高超声速进气道进行二维优化设计的设计软件系统。运用该系统,以总压恢复系数为目标,分别对3道激波外压、1道激波内压和3道激波外压、2道激波内压的二维高超声速进气道在设计点(飞行马赫数6.0,飞行高度25 km)进行了二维优化设计。设计算例表明,运用该系统对二维高超声速进气道进行优化设计是切实可行的。
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| 关 键 词： | 高超声速进气道 二维优化设计 拟Newton法 |
Study of Optimization Method for Two-Dimensional Hypersonic Inlet |
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| WANG Xiang-zhuan,ZHAN Hao,ZHU Jun.Study of Optimization Method for Two-Dimensional Hypersonic Inlet[J].Flight Dynamics,2009,27(4). |
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| Authors: | WANG Xiang-zhuan ZHAN Hao ZHU Jun |
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| Institution: | College of Aeronautics;Northwestern Polytechnical University;Xi'an 710072;China |
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| Abstract: | The optimization and design methods for the two-dimensional hypersonic inlet are done in this paper.The quasi-Newton method,structured grid and using Fluent software are combined to form a system to optimize and design the two-dimensional hypersonic inlet.By using this system to attain the general pressure recovering parameter,under the design point(flight Mach number is 6 and altitude is 25 km),the hypersonic inlet with 3 external shock compression ramps and 1 internal shock compression ramp,the hypersonic... |
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| Keywords: | hypersonic inlet two-dimensional optimization and design quasi-Newton method |
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