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首页> 外文期刊>The Aeronautical Journal >Experiments on the hypersonic turbulent shock-wave/boundary-layer interaction and the effects of surface roughness
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Experiments on the hypersonic turbulent shock-wave/boundary-layer interaction and the effects of surface roughness

机译：高超声速湍流波/边界层相互作用及表面粗糙度影响的实验

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摘要

An experimental investigation was performed to study the effects of surface roughness on the Mach 8.2 hypersonic turbulent shock-wave-boundary-layer interaction characteristics of a deflected control flap configuration. In particular, the surface pressure and heat transfer distribution along a quasi-2D ramp compression corner model was measured for flap angles between 0° and 38°, along with a Schlieren flow visualisation study. It was found that surface roughness, of scale 10% of the hinge-line boundary layer thickness, significantly increased the extent of the interaction, while increasing the magnitude of the peak pressure and heat flux just aft of reattachment. The incipient separation angle for a fully turbulent, Mach 8.2 boundary layer with a hinge line Reynolds number of 1.44 x 10~6, was estimated at 28-29°, reducing to between 19-22° with the introduction of laminar sub-layer scale surface roughness.
机译：进行了实验研究，以研究表面粗糙度对偏转控制襟翼构型的Mach 8.2高超声速湍流冲击波-边界层相互作用特性的影响。尤其是，在Schlieren流可视化研究的基础上，测量了在0°和38°之间的襟翼角时，沿准2D坡道压缩角模型的表面压力和传热分布。已经发现，表面粗糙度为铰链边界层厚度的10％，显着增加了相互作用的程度，同时又增加了重新安装后的峰值压力和热通量的幅度。铰链线雷诺数为1.44 x 10〜6的完全湍流的8.2马赫边界层的初始分离角估计为28-29°，随着层流子层尺度的引入减小到19-22°表面粗糙度。

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