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乘波飞行器构型方法研究
RESEARCH ON WAVERIDER CONFIGURATION METHOD
查看参考文献8篇
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文摘
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高超声速飞行中,随着马赫数的升高,波阻和摩阻增加,就会形成升阻比"屏障",而乘波飞行器构型是克服这一升阻比屏障的有效方法.本文提出了一种变楔角楔/椭圆锥乘波体构型方法,并基于前体/进气道一体化设计思想,生成了高超声速乘波飞行器构型.经数值计算与实验验证,与传统锥形流场生成的乘波体相比,该方法生成的乘波体不仅具有高升阻比,而且能为发动机提供所需的高温高压均匀来流. |
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其他语种文摘
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In hypersonic flow, as the increase of Mach number, the wave drag and friction drag also enlarge, and this will form a hysonic L/D "barrier". But waverider can efficiently overcome this "barrier". In this paper we develop a wedge-elliptical cone waverider configuration method, study on front body-scramjet engine integration design, and create a hypersonic waverider. In terms of numerical result and wind test data, it is different from traditional waveriders that this waverider can offer not only high L/D ratio, but also the uniform flow field with high temperature and high press which is requireed by scramjet engine. |
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来源
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力学学报
,2004,36(5):513-519 【核心库】
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关键词
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乘波飞行器
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变楔角楔/椭圆锥乘波体
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气动力
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升阻比
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地址
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中国科学院力学研究所, 高温气体动力学重点实验室, 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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0459-1879 |
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学科
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力学 |
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文献收藏号
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CSCD:1689925
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参考文献 共
8
共1页
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1.
Bowcutt K G. Viscous optimized wavriders.
Viscous optimized wavriders. AIAA Paper 87-0272,1987
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被引
1
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2.
Rasmussen M L. Waverider configurations derived from inclined circular and elliptic cones.
J of Spacecraft and Rockets,1980,17(6):537-545
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被引
38
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3.
Sobieczky H. Hypersonic waverider design from given shock waves.
Proceedings of the 1st International Hypersonic Waverider Symposium,1990:17-29
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被引
1
次
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4.
Miller R W. Experimental verification of the osculating cones method for two waverider forebodies at Mach 4 and 6.
Experimental verification of the osculating cones method for two waverider forebodies at Mach 4 and 6. AIAA Paper 98-0682,1998
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被引
1
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5.
O'Neill M K L. Design tradeoffs on scramjet engine integrated hypersonic waverider vehicles.
J of Aircraft,1993,30(6):943-952
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被引
9
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6.
汪家芸. 飞行器总体优化设计.
飞行器总体优化设计,1986
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被引
2
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7.
王发民. 高超声速升力体气动力气动热数值计算.
空气动力学报,2001,19(4):70-76
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被引
1
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8.
刘嘉. 高超声速飞行器前体压缩性能研究.
应用数学和力学,2004,25(1):85-93
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被引
3
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