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高超声速飞行器前体压缩性能研究
Alternative TitleForebody Compressibility Research of Hypersonic Vehicle
刘嘉; 姚文秀; 雷麦芳; 王发民
Source Publication应用数学和力学
2004-01-15
Volume25Issue:1Pages:85-92
ISSN1000-0887
Abstract用数值模拟的方法研究了高超声速飞行器前体不同型面与进气性能的关系,分析了二级压缩构型在不同压缩角组合和来流攻角下的流场品质和产生的压缩效果.研究结果表明,对于高超声速飞行器,采用多级压缩的前体构型可以得到较好的预压缩效果和优良的流场品质;同时,攻角和不同的压缩角组合会对压缩性能产生影响.因此,采用多级压缩的前体构型、优化各级压缩角的组合是决定飞行器前体预压缩性能的重要因素,同时也是开展前体/发动机一体化设计的关键.
Keyword高超声速飞行器 一体化设计 压缩性
Indexed ByCSCD
Language中文
CSCD IDCSCD:1499689
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/42332
Collection力学所知识产出(1956-2008)
Corresponding Author刘嘉
Recommended Citation
GB/T 7714
刘嘉,姚文秀,雷麦芳,等. 高超声速飞行器前体压缩性能研究[J]. 应用数学和力学,2004,25(1):85-92.
APA 刘嘉,姚文秀,雷麦芳,&王发民.(2004).高超声速飞行器前体压缩性能研究.应用数学和力学,25(1),85-92.
MLA 刘嘉,et al."高超声速飞行器前体压缩性能研究".应用数学和力学 25.1(2004):85-92.
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