摘要
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.
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.
基金
Supported by the National Natural Science Foundation of China under Grant Nos 90205025, 19872069, 170176033, and 10502052, and the Informatization Construction of Knowledge Innovation Projects of Chinese Academy of Sciences under Grant No INF 105-SCE. The authors would like to thank the State Key Laboratory of Scientific and Engineering Computing （LSEC） and Supercomputing Centre of Chinese Academy of Sciences （SCCAS） for providing computer time. The authors would like to thank Professor Zhou Heng and Professor Luo Jisheng of Tianjin University for helpful discussion.
