本文探讨了一种新的激波——非定常边界层相互干扰现象。
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。
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.
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.
实验结果表明，在本实验范围内，激波边界层干扰中的上游影响区都呈现出柱形区或锥形区特性；
The results show that the conical or cylindrical upstream influence region appears, in the interactions for all models and Mach numbers.
实验结果表明，在本实验范围内，激波边界层干扰中的上游影响区都呈现出柱形区或锥形区特性；
The results show that the conical or cylindrical upstream influence region appears, in the interactions for all models and Mach numbers.
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