| Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator | |
Huang TL(黄庭隆)1,2; Yue LJ(岳连捷)1,2 ; Ma SH(马生虎)1,2; Zhang QF(张启帆)1; Zhang, Peng3; Zhang XY(张新宇)1,2
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| Corresponding Author | Yue, Lianjie([email protected]) |
| Source Publication | CHINESE JOURNAL OF AERONAUTICS
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| 2020-12-01 | |
| Volume | 33Issue:12Pages:3176-3188 |
| ISSN | 1000-9361 |
| Abstract | Numerical simulation and theoretical analysis were conducted to study the hysteresis inside scramjet isolator during the reciprocating process of back pressure variation. It is revealed that only a regular reflection is theoretically possible for two leading shocks when the inflow Mach number is greater than 2.0, and no hysteresis can occur in the transition between shock reflection types. Nevertheless, wall suction, gas injection, and background waves cause non-uniformity of the incoming flow and would make hysteresis possible. Besides the classical hysteresis in the transition between shock reflection, new kinds of hysteresis were found in both the deflection angle of separated boundary layer and the location of the shock train. Moreover, the occurrence of hysteresis in the deflection angle of the separated boundary layer is accompanied with the shock reflection hysteresis. In the case with background waves or gas injection, hysteresis in the starting position of leading shock was observed too. As back pressure decreases, the leading shock does not follow the same path as that as the back pressure increases, and it is anchored at the location where the background shock or the injection interacts with the leading shock. It is inferred that, if two strong adverse pressure gradient regions move towards and interact with each other, hysteresis will take place when they start to separate. (c) 2020 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). |
| Keyword | Adverse pressure gradient Back pressure Hysteresis effects Non-uniform flow Shock train |
| DOI | 10.1016/j.cja.2020.04.019 |
| Indexed By | SCI ; EI ; CSCD |
| Language | 英语 |
| WOS ID | WOS:000616696900017 |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Natural Science Foundation of China[11672309] ; National Natural Science Foundation of China[11472279] ; Central Research Grant (G-YBGA) ; Central Research Grant (G-YBXN) |
| Funding Organization | National Natural Science Foundation of China ; Central Research Grant (G-YBGA) ; Central Research Grant (G-YBXN) |
| Classification | 二类/Q1 |
| Ranking | 1 |
| Contributor | Yue, Lianjie |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/86044 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Chinese Acad Sci, State Key Lab Hightemp Gas Dynam, Inst Mech, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 3.Hong Kong Polytech Univ, Dept Mech Engn, Hong Kong, Peoples R China |
| Recommended Citation GB/T 7714 | Huang TL,Yue LJ,Ma SH,et al. Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator[J]. CHINESE JOURNAL OF AERONAUTICS,2020,33,12,:3176-3188.Rp_Au:Yue, Lianjie |
| APA | 黄庭隆,岳连捷,马生虎,张启帆,Zhang, Peng,&张新宇.(2020).Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator.CHINESE JOURNAL OF AERONAUTICS,33(12),3176-3188. |
| MLA | 黄庭隆,et al."Numerical investigation on flow nonuniformity-induced hysteresis in scramjet isolator".CHINESE JOURNAL OF AERONAUTICS 33.12(2020):3176-3188. |
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| Jp2020526.pdf（3937KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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