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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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