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.
LI Xin-Liang;FU De-Xun;MA Yan-Wen. 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.
LI Xin-Liang, FU De-Xun, MA Yan-Wen. Direct Numerical Simulation of a Spatially Evolving Supersonic Turbulent Boundary Layer at Ma=6. Chin. Phys. Lett., 2006, 23(6): 1519-1522.
2006, Vol. 23 
