A method for analyzing the rotating turbulence boundary layer flow was presented.
本文通过计算分析了旋转湍流边界层。
Surface pressure distribution can be used to describe the airfoil boundary layer flow well.
可用于表面压力分布以及描述翼型边界层流的。
In the direct numerical simulation of supersonic boundary layer flow, the outlet boundary condition will strongly effect the computational results.
在超声速边界层的计算中,出口处边界条件的好坏会影响计算结果。
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