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Design methodology for shape transition inlets based on constant contraction of discrete streamtubes
Xiao YB(肖雅斌); Yue LJ(岳连捷); Ma SH; Zhang XY(张新宇); Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, 15 Beisihuanxi Rd, Beijing 100864, Peoples R China.
Source PublicationPROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING
2016
Volume230Issue:8Pages:1496-1506
ISSN0954-4100
AbstractIn this paper we propose a design concept, i.e. constant contraction of discrete streamtubes, to develop a new design method for hypersonic inlets with shape transition, which enables the shape transition inlet to have high compression efficiency while keeping flow uniformity as much as possible. The method first divides the 3D flow field of the inlet into several groups of discrete streamtubes with constant contraction ratio. The axisymmetric flow within each stream tube is then optimized via computational fluid dynamics to have high compression efficiency, and these discrete streamtube groups are finally assembled together by matching their shock wave reflection positions to form a 3D inlet flow field with weak crossflow. This method can be used for the design of shape transition inlets with specified entrance/exit sections. To validate the present methodology, we design a rectangular-to-circular inlet with a design point of Ma 6 and a takeover point of Ma 4, and examine numerically the flow structure and the inlet performances.
KeywordHypersonic Inlet Shape Transition Inward Turning Scramjet Design Method
DOI10.1177/0954410015613112
URL查看原文
Indexed BySCI ; EI
Language英语
WOS IDWOS:000378571900011
WOS KeywordHypersonic inlet ; shape transition ; inward turning ; scramjet ; design method
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace ; Engineering, Mechanical
Funding OrganizationThe author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: This work was supported by the National Natural Science Foundation of China (Grant No. 91216115 and 11472279).
DepartmentLHD高超声速推进技术
ClassificationQ3
RankingTrue
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/59571
Collection高温气体动力学国家重点实验室
Corresponding AuthorYue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, 15 Beisihuanxi Rd, Beijing 100864, Peoples R China.
Recommended Citation
GB/T 7714
Xiao YB,Yue LJ,Ma SH,et al. Design methodology for shape transition inlets based on constant contraction of discrete streamtubes[J]. PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING,2016,230(8):1496-1506.
APA 肖雅斌,岳连捷,Ma SH,张新宇,&Yue, LJ .(2016).Design methodology for shape transition inlets based on constant contraction of discrete streamtubes.PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING,230(8),1496-1506.
MLA 肖雅斌,et al."Design methodology for shape transition inlets based on constant contraction of discrete streamtubes".PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING 230.8(2016):1496-1506.
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