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。
In this paper, a new type of interaction of a moving shock with an unsteady boundary layer had been studied theoretically and experimentally.
本文探讨了一种新的激波——非定常边界层相互干扰现象。
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。
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。
The internal flow fields in scramjet are very complex, due to the interaction of shock waves, expansion waves, boundary layer and strong reactions.
超燃冲压发动机的内部流场很复杂，存在激波、膨胀波、附面层和剧烈的化学反应等相互作用，给数值模拟带来很大的困难。
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。
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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