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Boundary-Layer Instability Measurements in a Mach-6 Quiet Tunnel
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机译：Mach-6安静隧道中的边界层不稳定性测量
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摘要
Several experiments have been performed in the Boeing/AFOSR Mach-6 Quiet Tunnel at Purdue University. A 7 degree half angle cone at 6 degree angle of attack with temperature-sensitive paint (TSP) and PCB pressure transducers was tested under quiet flow. The stationary crossflow vortices appear to break down to turbulence near the lee ray for sufficiently high Reynolds numbers. Attempts to use roughness elements to control the spacing of hot streaks on a flared cone in quiet flow did not succeed. Roughness was observed to damp the second-mode waves in areas influenced by the roughness, and wide roughness spacing allowed hot streaks to form between the roughness elements. A forward-facing cavity was used for proof-of-concept studies for a laser perturber. The lowest density at which the freestream laser perturbations could be detected was 1.07 x 10(exp -2) kilograms per cubic meter. Experiments were conducted to determine the transition characteristics of a streamwise corner flow at hypersonic velocities. Quiet flow resulted in a delayed onset of hot streak spreading. Under low Reynolds number flow hot streak spreading did not occur along the model. A new shock tube has been built at Purdue. The shock tube is designed to create weak shocks suitable for calibrating sensors, particularly PCB-132 sensors. PCB-132 measurements in another shock tube show the shock response and a linear calibration over a moderate pressure range.
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机译：普渡大学的波音/ AFOSR Mach-6安静隧道中进行了一些实验。在安静流动下测试了6度攻角下的7度半角锥和热敏涂料（TSP）和PCB压力传感器。对于足够高的雷诺数，静止的横流涡流似乎分解成回风附近的湍流。尝试使用粗糙度元素来控制静流中扩口圆锥体上热条纹的间距并没有成功。观察到粗糙度在受粗糙度影响的区域中阻尼了第二模式波，并且宽的粗糙度间隔允许在粗糙度元件之间形成热条纹。前向腔用于激光干扰器的概念验证研究。可以检测到自由流激光干扰的最低密度是每立方米1.07 x 10（exp -2）千克。进行实验以确定在高超声速下的流向角流的过渡特性。安静的流动导致热条纹扩散的开始延迟。在低雷诺数流量下，沿模型未出现热条纹扩展。普渡大学建造了新的减震管。减震管旨在产生微弱的震动，适用于校准传感器，尤其是PCB-132传感器。在另一个冲击管中进行的PCB-132测量显示了在中等压力范围内的冲击响应和线性校准。
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