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Alternative TitleDesign of scramjet nozzle based on streamline tracing technique
卢鑫; 岳连捷; 肖雅彬; 张新宇
Source Publication推进技术
Other AbstractTo design the exhaust system for scramjet with three-dimensional flowpath,a method for designing three-dimensional scramjet nozzle was developed.It employed streamline tracing technique based on flowfield of axisymmetric nozzle with optimum thrust.According to a typical hypersonic flight condition,an inviscid nozzle with rectangular entrance of 50mm×50mm,length of 560mm and height of exit 147mm was constructed and then the boundary layer correction was applied.Inviscid and viscous flowfields were computed on the design point to get thrust and lift of the nozzle.Compared with two different nozzles constructed with straight walls,it is found that nozzle designed by streamline tracing technique can significantly increase the thrust and the viscous force is an important factor to decrease the thrust
Keyword三维尾喷管设计 流线追踪 超燃冲压发动机
Subject Area力学
Indexed ByEI ; CSCD
Funding Organization国家自然科学基金资助项目(90716014,10525212)
Citation statistics
Cited Times:7[CSCD]   [CSCD Record]
Document Type期刊论文
Corresponding Author卢鑫
Recommended Citation
GB/T 7714
卢鑫,岳连捷,肖雅彬,等. 超燃冲压发动机尾喷管流线追踪设计[J]. 推进技术,2011,32(1):91-96.
APA 卢鑫,岳连捷,肖雅彬,&张新宇.(2011).超燃冲压发动机尾喷管流线追踪设计.推进技术,32(1),91-96.
MLA 卢鑫,et al."超燃冲压发动机尾喷管流线追踪设计".推进技术 32.1(2011):91-96.
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