DNS of compressible turbulent boundary layer over a blunt wedge
DNS of compressible turbulent boundary layer over a blunt wedge
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DOI：
10.1360/03yw0300
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发表时间：
2005-04
影响因子：
6.4
通讯作者：
李新亮;傅德薰
中科院分区：
文献类型：
--
作者：
李新亮;傅德薰
本文对钝楔上可压缩边界层的空间演化进行了直接数值模拟。自由流马赫数为6，壁面吹吸产生的扰动源位于声速点下游。研究了统计结果，并与不可压缩平板边界层的结果进行了比较。研究了平均压力梯度对涡旋结构的影响。
Direct numerical simulation of spatially evolving compressible boundary layer over a blunt wedge is performed in this paper. The free-stream Mach number is 6 and the disturbance source produced by wall blowing and suction is located downstream of the sound-speed point. Statistics are studied and compared with the results in incompressible flat-plate boundary layer. The mean pressure gradient effects on the vortex structure are studied.