However, no thorough investigation has been made on shock wave boundary layer interaction in compressor cascades and only a few papers on this topic have been published.
然而迄今为止，尚未深入进行过压气机叶栅激波附面层相互作用的研究，发表的文献极少。
One of the more severe fluctuating pressure environments encountered in supersonic or hypersonic flows is the shock wave oscillation driven by interaction of a shock wave with boundary layer.
在超声速或高超声速绕流中，一种很严重的脉动压力环境是由激波边界层相互作用引起的激波振荡。
It is shown by calculation and analysis that the main form of the interaction in compressor cascades is the interaction between shock wave and turbulent boundary layer in channels.
作者经过计算和分析，说明压气机叶栅流中主要的相互作用形式是叶栅槽道中激波和湍流附面层的相互作用。
It has been confirmed by experiments that the boundary layer suction can efficiently eliminate the separation due to interaction of a reflected shock wave with the wall boundary layer.
实验证实了边界层抽吸可以有效地减小激波与壁面边界层相互作用所产生的分离现象。
Wall heat transfer fluctuations have been measured using a platinum film resistance thermometer in forward facing steps induced shock wave and turbulent boundary layer interaction fields.
用铂膜电阻温度计测量了前向台阶诱导激波与湍流边界层相互作用流场中的表面热流率脉动。
This paper presents the surface characteristics of the inter-action between shock wave and turbulent boundary layer induced by sharp fin with emphasis on Mach number effects.
本文介绍了尖前缘翼诱导激波和湍流边界层干扰流场壁面特性，着重强调马赫数影响。
The location of the shock wave will be larger move, even from interior layer to the boundary layer when the boundary conditions change smaller.
得出了在一定的情况下，当边界条件作微小变化时，激波的位置将作较大的变化，甚至由内层转到边界层。
The strong interaction between shock wave and boundary layer in the internal duct is like a bottleneck to the start of the inlet.
内收缩段内的激波与边界层的干扰较强，成为进气道起动的瓶颈。
The strong interaction between shock wave and boundary layer in the internal duct is like a bottleneck to the start of the inlet.
内收缩段内的激波与边界层的干扰较强，成为进气道起动的瓶颈。
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