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.
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。
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.
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。
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.
高时空分辨率的NPLS图像再现了激波、膨胀波、边界层及尾迹等流场结构。
NPLS images at high spatiotemporal resolution reveal shockwave, expansion wave, boundary layer and wake in the flow.
其次，研究了当激波在区间的边界附近和内部的激波解。
Secondly, the shock solutions as the shock layer near the boundary and interior of the interval are studied.
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。
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.
本文对一般具有不规则边界的含复杂激波系的火箭导弹射流冲击流场初边值问题的物理解进行了计算。
The physical solution of the initial and boundary problems of the rocket and missile impingement with complex shock structures in arbitrary bounded flow fields has been calculated in this paper.
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.
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 location of the shock wave will be larger move, even from interior layer to the boundary layer when the boundary conditions change smaller.
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.
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。
The strong interaction between shock wave and boundary layer in the internal duct is like a bottleneck to the start of the inlet.
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