| 压缩拐角激波/湍流边界层干扰特性分析 |
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| 引用本文： | 潘宏禄,马汉东,王强.压缩拐角激波/湍流边界层干扰特性分析[J].计算物理,2008,25(5):549-554. |
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| 作者姓名： | 潘宏禄 马汉东 王强 |
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| 作者单位： | 航天空气动力技术研究院, 北京 100074 |
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| 基金项目： | 国家重点基础研究发展计划(973计划) |
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| 摘 要： | 用大涡模拟方法对Mach数3.0下的压缩拐角激波/湍流边界层干扰问题进行数值研究.对拐角上游平板区域边界层转捩及湍流进行模拟,设定平板区域长度,使得转捩过程于平板区域发生并充分完成,从而在拐角处产生激波/湍流边界层相互干扰,研究激波/湍流边界层的作用机理.研究表明:流场能够在非定常扰动激励下迅速转捩,并于平板区发展为完全湍流;湍流边界层与激波相互作用过程中,拐角附近分离区较层流情况明显减小;展向不同区域分离区大小差异较大,局部区域分离现象消失.
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| 关 键 词： | 湍流 转捩 超声速边界层 压缩拐角 亚格子尺度模型 |
| 收稿时间： | 2007-05-29 |
| 修稿时间： | 2007-09-20 |
Transition and Turbulence/Shock Interaction in a Supersonic Boundary Layer Flow |
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| PAN Honglu,MA Handong,WANG Qiang.Transition and Turbulence/Shock Interaction in a Supersonic Boundary Layer Flow[J].Chinese Journal of Computational Physics,2008,25(5):549-554. |
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| Authors: | PAN Honglu MA Handong WANG Qiang |
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| Institution: | China Academy of Aerospace Aerodynamics, Beijing 100074, China |
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| Abstract: | Shock/turbulent boundary layer interaction(STBLI) in a M∞=3.0 supersonic compression ramp flow are studied using a spatial large eddy simulation method. At upstream, flat plate transition and developed turbulent boundary layer are simulated in which Shock/turbulent boundary layer interaction shows at the ramp. Analysis on mechanism of turbulent boundary layer/shock interaction indicates that linear unstable disturbance leads transition rapidly. In the process of STBLI, average separation range of the ramp is smaller than that in the laminar flow. However, extent of the separation shows different characteristics in different span-wise positions due to high velocity strip and low velocity strip. |
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| Keywords: | turbulence transition supersonic boundary layer ramp subgrid scale mode |
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