高超声速边界层流动转捩研究

IMECH-IR > 力学所知识产出(1956-2008)

	高超声速边界层流动转捩研究
Alternative Title	Stability and Transition of Hypersonic Boundary Layer Flow
	刘嘉; 雷麦芳; 姚文秀; 王发民
Source Publication	计算物理
	2004-01-25
Volume	21 Issue:1 Pages:61-67
ISSN	1001-246X
Abstract	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.
Keyword	高超声速流动稳定性分析转捩
Indexed By	CSCD
Language	中文
CSCD ID	CSCD:1565822
Citation statistics	Cited Times:3[CSCD] [CSCD Record]
Document Type	期刊论文
Identifier	http://dspace.imech.ac.cn/handle/311007/42200
Collection	力学所知识产出(1956-2008)
Corresponding Author	刘嘉
Recommended Citation GB/T 7714	刘嘉,雷麦芳,姚文秀,等. 高超声速边界层流动转捩研究[J]. 计算物理,2004,21,1,:61-67.
APA	刘嘉,雷麦芳,姚文秀,&王发民.(2004).高超声速边界层流动转捩研究.计算物理,21(1),61-67.
MLA	刘嘉,et al."高超声速边界层流动转捩研究".计算物理 21.1(2004):61-67.

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