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Experimental Study of Shock Impingement on a Blunt Leading Edge with Application to Hypersonic Inlet Design

机译：应用于高超声速进气道设计的钝头前缘冲击冲击试验研究

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摘要

An experimental study was made of the interaction of an oblique shock with the bow shock of blunt leading edge. The interactions were classified according to the interference patterns described by Edney. Peak heating rates 5.5 times those of the blunt leading edge alone were studied. All interactions appeared to be unsteady except when the slipstream of the interaction passed above the blunt leading edge. (Author)

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Craig, R. R.; Ortwerth, P. J.;
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年度 1971
页码 p.1-43
总页数 43
原文格式 PDF
正文语种 eng
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关键词
Ramjet inlets ; Shock waves ; Hypersonic characteristics ; Blunt bodies ; Leading edge ; Wind tunnel models ; Model tests ; Heat transfer ; Pressure;

机译：冲压发动机进气道;冲击波;高超声速特性;钝体;前缘;风洞模型;模型试验;传热;压力;

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2. Hypersonic Shock Wave Interactions on a V-Shaped Blunt Leading Edge [J] . Xiao Fengshou, Li Zhufei, Zhang Zhiyu, AIAA Journal . 2018,第1期

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3. Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed [J] . Bibin John, Vinayak Kulkarni Computers & Fluids . 2014,第Null期

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4. Experimental Investigation of Leading Edge Bluntness Effects on Hypersonic Tow-dimensional Inlet [C] . Zhang Hong-jun, Shen Qing Asia-Pacific International Symposium on Aerospace Technology . 2015

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5. Experimental Investigation of Leading Edge Jet Impingement with Varying Jet Geometries and Inlet Supply Conditions for Turbine Cooling Applications [D] . Jordan, C. Neil. 2012

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6. DSMC Simulation and Experimental Validation of Shock Interaction in Hypersonic Low Density Flow [O] . Hong Xiao, Yuhe Shang, Di Wu -1

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7. Experimental Investigation of Leading Edge Bluntness Effects on Hypersonic Tow-dimensional Inlet [O] . Hong-jun Zhang, Qing Shen 2015

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8. Two and three-dimensional shock-shock interactions on the blunt leading edges of the hypersonic inlets [R] . Singh, D. J., Kumar, Ajay, Tiwari, S. N. 1991

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Experimental Study of Shock Impingement on a Blunt Leading Edge with Application to Hypersonic Inlet Design

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