Effects of nozzle exit wall thickness on the formation of compressible vortex rings

机译：喷嘴出口壁厚对可压缩涡流环形成的影响

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An experimental study was conducted to assess therneffects of fine variations of the nozzle exit wallrnthickness on the flow behaviour and characteristics ofrncompressible vortex rings. The experiments used arnconstant cross section driven section with a 30mmrninternal diameter and three exit wall thicknesses: 2mm,rn4mm, and 8mm. Three driver pressures were used, 4bar,rn8bar, 12bar, with the driven gas at ambient conditions.rnThe shock wave Mach numbers generated inside therntube were 1.34, 1.54, and 1.66. High speed schlierenrnand shadowgraph photography were employed tornvisualize the vortex ring flow features and qualitativernand quantitative data was extrapolated from the images.

机译：进行了一项实验研究，以评估喷嘴出口壁厚度的细微变化对可压缩涡流环的流动行为和特性的影响。实验使用内径为30mm，三种出口壁厚分别为2mm，rn4mm和8mm的非恒定横截面驱动截面。在环境条件下，使用三种驱动压力，分别为4bar，rn8bar，12bar。在管内产生的冲击波马赫数分别为1.34、1.54和1.66。利用高速schlierenrnand阴影照片摄影对涡流环流特征进行可视化，并从图像中推断出定性和定量数据。

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来源
《New beginnings: challenges for aerospace innovation》|2009年|p.1-7|共7页
会议地点 Manchester(GB)
作者
Mariani R.; Kontis K.;
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作者单位

University of Manchester, Manchester, M60 1QD, UK;

University of Manchester, Manchester, M60 1QD, UK;

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原文格式 PDF
正文语种 eng
中图分类航空、航天技术的研究与探索;
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4. Effects of nozzle exit wall thickness on the formation of compressible vortex rings [C] . Mariani R., Kontis K. CEAS European air and space conference . 2009

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Effects of nozzle exit wall thickness on the formation of compressible vortex rings

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