| 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.
|
| 发表期刊 | PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING
 |
| 2016
|
| 卷号 | 230期号:8页码:1496-1506 |
| ISSN | 0954-4100
|
| 摘要 | 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. |
| 关键词 | Hypersonic Inlet
Shape Transition
Inward Turning
Scramjet
Design Method
|
| DOI | 10.1177/0954410015613112
|
| URL | 查看原文
|
| 收录类别 | SCI
; EI
|
| 语种 | 英语
|
| WOS记录号 | WOS:000378571900011
|
| 关键词[WOS] | Hypersonic inlet
; shape transition
; inward turning
; scramjet
; design method
|
| WOS研究方向 | Engineering
|
| WOS类目 | Engineering, Aerospace
; Engineering, Mechanical
|
| 项目资助者 | 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).
|
| 课题组名称 | LHD高超声速推进技术
|
| 论文分区 | Q3
|
| 力学所作者排名 | True
|
| 引用统计 |
|
| 文献类型 | 期刊论文
|
| 条目标识符 | http://dspace.imech.ac.cn/handle/311007/59571
|
| 专题 | 高温气体动力学国家重点实验室
|
| 通讯作者 | Yue, LJ (reprint author), Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, 15 Beisihuanxi Rd, Beijing 100864, Peoples R China. |
推荐引用方式
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.
|
修改评论