DNS and analysis of a spatially evolving hypersonic turbulent boundary layer over a flat plate at Mach 8

Direct numerical simulation is investigated for hypersonic flat plate with Ma∞=8 and Tw/T∞=10.03. Present computation covers the procedure from laminar flow to final full developed turbulent flow. A deliberate analysis of turbulent statistics characteristics has been presented in this paper. The results show that, with present computational conditions, mean velocity profile in core region of turbulence satisfies logarithm law, and Karman constant is kept here. Because of the wall temperature is high, so the local sound speed increases and turbulent Mach number decrease, as the results that intrinsic compressible effects is not strong. The strong Reynolds analogy is still validity with small deviation of value compare to traditional results. And Morkovin's hypothesis is still true in present study. Extended self-similarity is also tested and verified, The shrinking of the ESS range of scales is captured by comparing to low Mach number flow. Finally, near-wall streaks and iso-vorticity are also tested and analyzed.