IMECH-IR  > 力学所知识产出(1956-2008)
扩压段对高超声速推进风洞起动的影响
Alternative TitleInvestigation for effect of supersonic diffusers on the start of the hypersonic propulsion test facility
陈立红; 张新宇; 顾洪斌
Source Publication推进技术
2004
Volume25Issue:5Pages:430-434
ISSN1001-4055
Abstract高超声速推进风洞是进行超燃冲压发动机模型地面模拟的重要试验设备.其中,扩压段的设计非常重要,它不是孤立的,而与主流系统和引射系统密切相关.通过对不同几何形状的扩压段在不同安装位置进行调试,研究在风洞起动过程中整个系统流动状态的演变规律,探索扩压段的优化设计.实验表明,扩压段应安装在距主喷管较近的位置,并具有与主喷管相匹配的入口面积和形状.扩压段的形状应设计成能使主气流通过一系列斜激波串减速的通道.扩压段应具有一定的长度以保证主气流减速到一定程度.
Keyword超音速冲压喷气发动机 超高速风洞 超声速扩压段 模型
Subject Area力学
Indexed ByCSCD ; EI
Language中文
CSCD IDCSCD:1653427
Citation statistics
Cited Times:12[CSCD]   [CSCD Record]
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/16745
Collection力学所知识产出(1956-2008)
Recommended Citation
GB/T 7714
陈立红,张新宇,顾洪斌. 扩压段对高超声速推进风洞起动的影响[J]. 推进技术,2004,25,5,:430-434.
APA 陈立红,张新宇,&顾洪斌.(2004).扩压段对高超声速推进风洞起动的影响.推进技术,25(5),430-434.
MLA 陈立红,et al."扩压段对高超声速推进风洞起动的影响".推进技术 25.5(2004):430-434.
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