Abstract Experiments were performed within the Rutgers University Mach 3.4 supersonic wind tunnel to quantify the turbulent boundary layer in the test section, using stereoscopic particle image velocimetry (SPIV). Seeding of the tunnel was accomplished using atomized mineral oil, resulting in a Stokes number of 0.09. The Reynolds number based on momentum thickness and the friction-velocity Reynolds number were 64,000 and 4320, respectively, marking this as a high Reynolds number boundary layer. SPIV measurements were capable of resolving the mean velocity profile, along with turbulence quantities, permitting comparison against the known literature. Furthermore, the convection of vorticity concentrations representing hairpin vortices was observed within instantaneous vector fields. The resulting Reynolds stresses demonstrate that the boundary layer had typical values of anisotropy, while comparing well with data obtained within a slightly adverse pressure gradient. This was particularly noticeable from the trends in the Reynolds stresses, which exhibited higher-than-expected peak levels. These data provide a unique measurement of a supersonic turbulent boundary layer at Reynolds numbers not often encountered within existing data sets. Graphic abstract

中文翻译：

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使用立体粒子图像测速法测量 3.4 马赫湍流边界层

摘要 在罗格斯大学 3.4 马赫超音速风洞内进行了实验，以使用立体粒子图像测速法 (SPIV) 量化测试段中的湍流边界层。使用雾化矿物油完成隧道的播种，导致斯托克斯数为 0.09。基于动量厚度的雷诺数和摩擦速度雷诺数分别为 64,000 和 4320，标志着这是一个高雷诺数边界层。SPIV 测量能够解析平均速度剖面以及湍流量，从而可以与已知文献进行比较。此外，在瞬时矢量场内观察到代表发夹涡的涡度浓度的对流。由此产生的雷诺应力表明边界层具有各向异性的典型值，同时与在略微不利的压力梯度内获得的数据进行了很好的比较。这在雷诺应力的趋势中尤为明显，其表现出高于预期的峰值水平。这些数据提供了在现有数据集中不常见的雷诺数下超音速湍流边界层的独特测量。图形摘要 这些数据提供了在现有数据集中不常见的雷诺数下超音速湍流边界层的独特测量。图形摘要 这些数据提供了在现有数据集中不常见的雷诺数下超音速湍流边界层的独特测量。图形摘要