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Comparison of some measurement techniques for shock-induced boundary layer separation

机译：震动引起的边界层分离的几种测量技术的比较

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摘要

Detailed results are presented concerning the position of separation and reattachment in case o shock/boundary-layer interaction. The tests were performed with a flat plate-24 deg-ramp configuration mounted between the vertical walls of the Trisonic Windtunnel Munich. The quality of schlieren method, pressure measurement technique, oil-flow visualization and laser Doppler anemometry is critically reviewed. The average thickness of the fully developed turbulent boundary layer just ahead of the ramp is δ_0=13 mm. The results show the location of separation and reattachment as a function of Mach and Reynolds number. Mach numbers ranging from 2.2 to 2.9, and unit Reynolds numbers from 29.10~16 m~-1 to 58.10~6 m~-1.
机译：给出了有关在冲击/边界层相互作用情况下分离和重新连接位置的详细结果。使用安装在Trisonic Windtunnel Munich垂直壁之间的平板24度坡道配置进行测试。严格审查了schlieren方法，压力测量技术，油流可视化和激光多普勒风速仪的质量。完全在斜坡前面的完全展开的湍流边界层的平均厚度为δ_0= 13 mm。结果表明分离和重新连接的位置是马赫数和雷诺数的函数。马赫数范围从2.2到2.9，雷诺数范围从29.10〜16 m〜-1到58.10〜6 m〜-1。

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