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高超声速飞行器前体压缩性能研究
Forebody Compressibility Research of Hypersonic Vehicle
查看参考文献8篇
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文摘
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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. |
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其他语种文摘
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Three kinds of forebody model of hypersonic vehicles were studied with numerical simula-tion method. It shows that the two-order compressive ramp model is the best selection among the three for its good evaluative parameters value at the cowl of the inlet. This model can provide higher value of flux coefficient and total pressure recovery coefficient and lower average Mach number com-pared with those of the other two models. Simultaneously different compressive angles may have dif-ferent effects. The configuration which the first order of compressive angle is 4° and the second 5° is the optimum combination. Furthermore factors such as attack angle were concerned. Better result may be obtained with a range of attack angles. Based on the work above the integrated design for forebody/inlet of a hypersonic vehicle was performed. The numerical result shows that this integrated model provides good flow field quality for inlet and engine work. |
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来源
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应用数学和力学
,2004,25(1):85-92 【核心库】
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关键词
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高超声速飞行器
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一体化设计
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压缩性
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地址
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中国科学院力学研究所LHD, 北京, 100080
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1000-0887 |
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学科
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航空 |
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文献收藏号
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CSCD:1499689
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