| Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion | |
Xue R1,2; Zheng X1; Yue LJ(岳连捷)2 ; Zhang SK3; Weng C4
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| Source Publication | ACTA ASTRONAUTICA
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| 2020-09-01 | |
| Volume | 174Pages:11-23 |
| ISSN | 0094-5765 |
| Abstract | In this study, the effect of wall-jet combustion on boundary layer transition and skin friction reduction was numerically investigated. To effectively capture the characteristics of boundary layer flow, the transition k - kl - w model was employed as the turbulence model and laminar finite-rate model was chosen as the combustion model. This numerical method was firstly validated by two sets of experimental results in open domain. After that, the research on wall-jet combustion was conducted and the numerical results showed that when injecting hydrogen in different directions, both the hydrogen self-ignition location and the skin friction on the wall were not altered significantly. When the injection angle to the airflow direction was increased to 30 degrees, the intensity of combustion was insufficient and the skin-friction coefficient would be increased. Meanwhile, boundary layer transition occurred in a relatively smaller Reynolds number at this condition. The variation of the wall-jet height would have a greater impact on both boundary layer transition and the skin friction. More components can diffuse to the lower wall as the height of the wall-jet was enlarged, which can make the process of boundary layer transition be postponed and the skin friction be reduced as well. Furthermore, greater skin-friction reduction would be achieved downstream the self-ignition location when the wall was adiabatic, while the original Reynolds numbers for boundary layer transition is the smallest if the wall temperature is set to 600 K. Finally, in order to simulate the effect of the back pressure on the combustion flow field, another injector is added near the exit at the upper wall to produce air-throttling flow jet. The results showed that altering back pressure nearly has little influence on boundary layer transition and the skin friction decreases with more air-throttling flow rate. |
| Keyword | Compressible boundary layer combustion Skin-friction reduction Boundary layer transition Transition k-kl-w model Hydrogen combustion |
| DOI | 10.1016/j.actaastro.2020.04.031 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000540350100002 |
| WOS Keyword | HEAT-TRANSFER ; PREDICTION ; HYDROGEN |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Organization | National Natural Science Foundation of China[51706170] ; China Postdoctoral Science Foundation[2019TQ0246] ; China Postdoctoral Science Foundation[2019M663734] ; Foundation of State Key Laboratory of Coal Combustion[FSKLCCA2004] ; Natural Science Basic Research Program of Shaanxi[2020JQ-007] ; Foundation of State Key Laboratory of High Temperature Gas Dynamics ; Foundation of State Key Laboratory of Turbulence & Complex Systems ; Fundamental Research Funds for the Central Universities[xzy012019053] ; Fundamental Research Funds for the Central Universities[xjh012019033] |
| Classification | 一类 |
| Ranking | 3 |
| Contributor | Xue, Rui ; Zheng, Xing |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/84724 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Xi An Jiao Tong Univ, Sch Aerosp, State Key Lab Strength & Vibrat Mech Struct, Shaanxi Engn Lab Vibrat Control Aerosp Struct, Xian 710049, Peoples R China; 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 3.Xian Modern Control Technol Res Inst, Xian 710065, Peoples R China; 4.Tongji Univ, Shanghai 200092, Peoples R China |
| Recommended Citation GB/T 7714 | Xue R,Zheng X,Yue LJ,et al. Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion[J]. ACTA ASTRONAUTICA,2020,174:11-23.Rp_Au:Xue, Rui, Zheng, Xing |
| APA | Xue R,Zheng X,岳连捷,Zhang SK,&Weng C.(2020).Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion.ACTA ASTRONAUTICA,174,11-23. |
| MLA | Xue R,et al."Numerical study on supersonic boundary-layer transition and wall skin friction reduction induced by fuel wall-jet combustion".ACTA ASTRONAUTICA 174(2020):11-23. |
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| Jp2020168.pdf（3912KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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