The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.

中文翻译：

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冲击波对前缘后掠角可变的平板边界层中流动的影响

对于马赫数为2的平板前缘的不同后掠角，通过实验研究了弱冲击波对沿流安装的平钝板边界层流的影响。进入流中的冲击波形式为通过设置在T-325风洞侧壁上的150×7×0.13-mm二维粗糙度产生N波的波幅。可以确认的是，当以零扫角入射N波到板的前缘时，在边界处观察到纵向涡旋的产生，伴随着脉动水平的增加和扰动的光谱成分的变化。层。风速数据表明，在“追赶”入射弱冲击波的影响下，当前缘的扫掠角从0度变为25度时，