| Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma = 6 |
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| 引用本文： | 李新亮 傅德薰 马延文. Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma = 6[J]. 中国物理快报, 2006, 23(6): 1519-1522 |
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| 作者姓名： | 李新亮 傅德薰 马延文 |
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| 作者单位： | LNM, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080 |
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| 摘 要： |
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| 关 键 词： | 直接数字模拟 空间进化 超声狂暴边界层 Navier-Stokes方程 |
| 收稿时间： | 2006-03-04 |
| 修稿时间： | 2006-03-04 |
Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma=6 |
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| LI Xin-Liang,FU De-Xun,MA Yan-Wen. Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma=6[J]. Chinese Physics Letters, 2006, 23(6): 1519-1522 |
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| Authors: | LI Xin-Liang FU De-Xun MA Yan-Wen |
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| Affiliation: | LNM, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080 |
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| Abstract: | Direct numerical simulation is carried out for a spatially evolving supersonic turbulent boundary layer at freestream Mach number 6. To overcome numerical instability, the seventh-order WENO scheme is used for the convection terms of Navier-Stokes equations, and fine mesh is adopted to minimize numerical dissipation. Compressibility effects on the near-wall turbulent kinetic energy budget are studied. The cross-stream extended self-similarity and scaling exponents including the near-wall region are studied. In high Mach number flows, the coherence vortex structures are arranged to be smoother and streamwised, and the hair-pin vortices are less likely tO OCCUr. |
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| Keywords: | 47.27.Eq 47.27.Nz 83.85.Pt |
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