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Transition prediction of a hypersonic boundary layer over a cone at small angle of attack——with the improvement of e^N method

查看全文 作  者:SU CaiHong1 & ZHOU Heng1,2 1 Department of Mechanics, Tianjin University, Tianjin 300072, China;2 Liu-Hui Center of Applied Mathematics, Nankai University and Tianjin University, Tianjin 300072, China 高影响力作者 出  处:《Science China(Physics,Mechanics & Astronomy)》索引2009年第52卷第1期,共9页高影响力期刊 基  金:Supported by the National Natural Science Foundation of China (Grant Nos. 10632050 and 90716007);the Special Foundation for the Authors of National Excellent Doctoral Dissertations (Grant No. 200328);the Foundation of Liu-Hui Center of Applied Mathematics of Nankai University and Tianjin University 摘  要:The problem of transition prediction for hypersonic boundary layers over a sharp cone has been studied in this work. The Mach number of the oncoming flow is 6, the cone half-angle is 5o,and the angle of attack is 1o. The conventional eN method is used, but the transition location so obtained is obviously incorrect. The reason is that in the conventional method, only the amplifying waves are taken into account, while in fact, for different meridians the decay processes of the disturbances before they begin to grow are different. Based on our own previous work, new interpretation and essential improvement for the eN method are proposed. Not only the amplification process but also the decay process is considered. The location, where by linear stability theory, the amplitude of disturbance wave is amplified from its initial small value to 1%, is considered to be the transition location. The new result for transition prediction thus obtained is found to be fairly satisfactory. It is also indicated that for the calculation of base flow, boundary layer equations can be used for a small angle of attack. Its computational cost is much smaller than those for DNS. 关 键 词:ANGLE of ATTACK CONE TRANSITION eN METHOD
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