| 可压缩湍流边界层近壁区马蹄涡的演化 |
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| 引用本文： | 史万里,葛宁,陈林,唐登斌.可压缩湍流边界层近壁区马蹄涡的演化[J].空气动力学学报,2011,29(6). |
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| 作者姓名： | 史万里 葛宁 陈林 唐登斌 |
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| 作者单位： | 1. 南京航空航天大学能源与动力学院,江苏南京,210016
2. 南京航空航天大学航空宇航学院,江苏南京,210016 |
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| 基金项目： | 国家自然科学基金(10772082) |
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| 摘 要： | 采用大涡模拟方法对可压缩槽道湍流进行了数值模拟.通过给定扰动波方法确定进口边界条件,很快得到了完全发展的湍流.利用动态亚格子模型、预处理技术以及高阶格式和方法,得到了精确的数值结果.计算得到的速度剖面和脉动分量与直接数值模拟的解进行了对比,验证了计算结果的可靠性.结果清楚地展示了湍流场中马蹄涡的生成和演化过程,包括对称涡腿、单侧涡腿的马蹄涡结构,以及流场中存在由亚谐波引起的拟序结构的交错现象.分析了湍流边界层近壁区可能出现的复杂的马蹄涡结构,及其涡结构形状也不严格对称的现象.
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| 关 键 词： | 大涡模拟 马蹄涡 拟序结构 湍流边界层 动态亚格子模型 |
The evolution of the horseshoe-shaped vortex in the near-wall region of compressible turbulent boundary layer |
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| SHI Wan-li
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GE Ning
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CHEN Lin
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TANG Deng-bin.The evolution of the horseshoe-shaped vortex in the near-wall region of compressible turbulent boundary layer[J].Acta Aerodynamica Sinica,2011,29(6). |
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| Authors: | SHI Wan-li GE Ning CHEN Lin TANG Deng-bin |
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| Institution: | SHI Wan-li1,GE Ning1,CHEN Lin2,TANG Deng-bin2(1.Nanjing University of Aeronautics and Astronautics,College of Energy and Power Engineering,Nanjing 210016,China,2.Nanjing University of Aeronautics and Astronautics,College of Aerospace Engineering,China) |
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| Abstract: | The full developed turbulent flow in channels was simulated using Large Eddy Simulation(LES) with a given disturbance wave in inlet boundary,after a short development section.The dynamic subgrid-scale model,the preconditioned algorithm and high-order scheme are used in computing.The numerical results are precise.The computed results showed good agreement with DNS,which included root mean square fluctuated velocity distribution and average velocity distribution.This shows the reliability of simulation.The re... |
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| Keywords: | large eddy simulation the horseshoe-shaped vortex coherent structures turbulent boundary layer dynamic subgrid-scale model |
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