| Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25 | |
Duan JY(段俊亦) ; Tong FL(童福林); Li XL(李新亮); Liu HW(刘洪伟)
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| Corresponding Author | Liu, Hongwei([email protected]) |
| Source Publication | CHINESE JOURNAL OF AERONAUTICS
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| 2023-09-01 | |
| Volume | 36Issue:9Pages:178-194 |
| ISSN | 1000-9361 |
| Abstract | The evolution characteristics of the mean skin friction beneath the supersonic turbulent boundary layer that interacts with incident shock waves at Mach 2.25 are analyzed using Direct Numerical Simulation (DNS). The separated and attached boundary layers in the interaction region that respectively correspond to 33.2 degrees and 28 degrees incident shock angles are considered. The mean skin friction recovery rate for the separated boundary layer is much gentler and distinctly less than that for the attached case where the skin friction completes its recovery within one boundary layer thick-ness. The novel mean skin friction decomposition method for compressible flows proposed by the recent research is applied in the interaction region to investigate the internal evolution characteristics quantitatively. The results reveal that the three decomposition components are distinctly unequal between the two cases. The contributions of the turbulent motions at different scales to the associated term are focused on using empirical mode decomposition technology. It indicates that the outer large-scale structures dominate separation and reattachment regions, while contributions from inner small-scale structures are limited. In contrast, contributions from the outer large-scale structures are dramatically reduced in the attached case, which results in the outer large-scale and inner small-scale motions being of equal importance.(c) 2023 Production and hosting by Elsevier Ltd. on behalf of Chinese Society of Aeronautics and Astronautics. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/ licenses/by-nc-nd/4.0/). |
| Keyword | Compressible flow Boundary layers Direct numerical simulation Shock waves Skin friction Turbulent flow |
| DOI | 10.1016/j.cja.2023.06.015 |
| Indexed By | SCI ; EI ; CSCD |
| Language | 英语 |
| WOS ID | WOS:001084134400001 |
| WOS Keyword | DIRECT NUMERICAL-SIMULATION ; WAVE STRUCTURE ; UNSTEADINESS |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Classification | 一类 |
| Ranking | 1 |
| Contributor | Liu, Hongwei |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/93151 |
| Collection | 高温气体动力学国家重点实验室 |
| Recommended Citation GB/T 7714 | Duan JY,Tong FL,Li XL,et al. Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25[J]. CHINESE JOURNAL OF AERONAUTICS,2023,36,9,:178-194.Rp_Au:Liu, Hongwei |
| APA | 段俊亦,童福林,李新亮,&刘洪伟.(2023).Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25.CHINESE JOURNAL OF AERONAUTICS,36(9),178-194. |
| MLA | 段俊亦,et al."Decomposition of mean skin friction in incident shock wave/turbulent boundary layer interaction flows at Mach 2.25".CHINESE JOURNAL OF AERONAUTICS 36.9(2023):178-194. |
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| Jp2023Fa056.pdf（6039KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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