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Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma=6 |
| LI Xin-Liang;FU De-Xun;MA Yan-Wen |
| LNM, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080 |
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| Cite this article: |
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LI Xin-Liang, FU De-Xun, MA Yan-Wen 2006 Chin. Phys. Lett. 23 1519-1522 |
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Abstract Direct numerical simulation is carried out for a spatially evolving supersonic turbulent boundary layer at free-stream 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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Published: 01 June 2006
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