Supersonic Base Flow Experiments in the Near Wake of a Cylindrical Afterbody
Supersonic Base Flow Experiments in the Near Wake of a Cylindrical Afterbody
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DOI：
10.2514/3.11953
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发表时间：
1993
期刊：
影响因子：
2.5
通讯作者：
J. Herrin;J. Dutton
中科院分区：
文献类型：
--
作者：
J. Herrin;J. Dutton
与均匀马赫 2.5 流对齐的圆柱体的近尾流已在专门为此目的设计的风洞中进行了实验研究。平均静压测量用于评估基础压力和接近分离的平均压力场的径向依赖性。此外，在整个近尾流（包括底座下游的大分离区域）中获得了双分量激光多普勒测速仪（LDV）测量。该研究的主要目的是更好地了解超音速基础流场中的复杂流体动力学过程，包括分离、剪切层发展、沿对称轴的重新附着以及尾流的后续发展
The near wake of a circular cylinder aligned with a uniform Mach 2.5 flow has been experimentally investigated in a wind tunnel designed solely for this purpose. Mean static pressure measurements were used to assess the radial dependence of the base pressure and the mean pressure field approaching separation. In addition, two-component laser Doppler velocimeter (LDV) measurements were obtained throughout the near wake including the large separated region downstream of the base. The primary objective of the research was to gain a better understanding of the complex fluid dynamic processes found in supersonic base flowfields including separation, shear layer development, reattachment along the axis of symmetry, and subsequent development of the wake