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高超声速边界层流动转捩研究
Stability and Transition of Hypersonic Boundary Layer Flow
查看参考文献9篇
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文摘
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针对高超声速飞行器前体预压缩性所需求的气动构型,开展了具有一级压缩效果的压缩面边界层的流动稳定性分析.采用有限体积法数值求解NS方程组得到基本流场,应用当地局部平行流假设和线性稳定性理论求解了扰动波参数的特征值问题.分析了来流马赫数M∞=6情况下二维扰动波的演化规律,并进一步关联扰动的空间放大率,结合EN方法进行了转捩预测. |
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其他语种文摘
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The stability analysis and transition prediction are proceeded for one' order compression ramp, which is the valuable configuration for the hypersonic vehicles. The finite volume method is used to solve the NS equations to get the basic flow field. The solution of the eigenvalue problem is obtained by using the linear stability theory under the assumption of local parallel flows.The first mode and the second mode unstable waves are found al the Mach number of 6. With the relation of the temporal and spatial amplification rates, the transition position is predicted by the EN method. |
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来源
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计算物理
,2004,21(1):61-67 【核心库】
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关键词
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高超声速流动
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稳定性分析
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转捩
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地址
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中国科学院力学研究所, 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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1001-246X |
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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:1565822
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参考文献 共
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