| 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 Publication | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING
 |
| 2016 | |
| Volume | 230Issue:8Pages:1496-1506 |
| ISSN | 0954-4100 |
| Abstract | In 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. |
| Keyword | Hypersonic Inlet Shape Transition Inward Turning Scramjet Design Method |
| DOI | 10.1177/0954410015613112 |
| URL | 查看原文 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000378571900011 |
| WOS Keyword | Hypersonic inlet ; shape transition ; inward turning ; scramjet ; design method |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace ; Engineering, Mechanical |
| Funding Organization | The 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). |
| Department | LHD高超声速推进技术 |
| Classification | Q3 |
| Ranking | True |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/59571 |
| Collection | 高温气体动力学国家重点实验室 |
| Corresponding Author | Yue, 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. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| a2016-156.pdf（1353KB） | 期刊论文 | 作者接受稿 | 开放获取 | CC BY-NC-SA | View Download | |
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment