| Effects of wall temperature on hypersonic shock wave/turbulent boundary layer interactions | |
Zhang J(张吉)1,2; Guo TB(郭同彪)1; Dang GL(党冠麟)3; Li XL(李新亮)1,2
| |
| Corresponding Author | Li, Xinliang([email protected]) |
| Source Publication | JOURNAL OF FLUID MECHANICS
 |
| 2024-08-14 | |
| Volume | 990Pages:35 |
| ISSN | 0022-1120 |
| Abstract | Wall temperature has a significant effect on shock wave/turbulent boundary layer interactions (STBLIs) and has become a non-negligible factor in the design process of hypersonic vehicles. In this paper, direct numerical simulations are conducted to investigate the wall temperature effects on STBLIs over a 34 degrees compression ramp at Mach number 6. Three values of the wall-to-recovery-temperature ratio (0.50, 0.75 and 1.0) are considered in the simulations. The results show that the size of the separation bubble declines significantly as the wall temperature decreases. This is because the momentum profile of the boundary layer becomes fuller with wall cooling, which means the near-wall fluid has a greater momentum to suppress flow separation. An equation based on the free-interaction theory is proposed to predict the distributions of the wall pressure upstream of the corner at different wall temperatures. The prediction results are generally consistent with the simulation results (Reynolds number Re-tau ranges from 160 to 675). In addition, the low-frequency unsteadiness is studied through the weighted power spectral density of the wall pressure and the correlation between the upstream and downstream. The results indicate that the low-frequency motion of the separation shock is mainly driven by the downstream mechanism and that wall cooling can significantly suppress the low-frequency unsteadiness, including the strength and streamwise range of the low-frequency motions. |
| Keyword | hypersonic flow shock waves turbulent boundary layers |
| DOI | 10.1017/jfm.2024.533 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:001289911800001 |
| WOS Keyword | DIRECT NUMERICAL-SIMULATION ; LOW-FREQUENCY UNSTEADINESS ; WAVE STRUCTURE ; SEPARATION ; TURBULENCE ; NUMBER ; FLOWS |
| WOS Research Area | Mechanics ; Physics |
| WOS Subject | Mechanics ; Physics, Fluids & Plasmas |
| Funding Project | National Key Research and Development Program of China[2019YFA0405300] ; Strategic Priority Research Program of Chinese Academy of Sciences[XDB0500301] ; National Natural Science Foundation of China[12232018] ; National Natural Science Foundation of China[91852203] ; National Natural Science Foundation of China[12072349] ; National Natural Science Foundation of China[12202457] |
| Funding Organization | National Key Research and Development Program of China ; Strategic Priority Research Program of Chinese Academy of Sciences ; National Natural Science Foundation of China |
| Classification | 一类/力学重要期刊 |
| Ranking | 1 |
| Contributor | Li, Xinliang |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/96323 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Chinese Acad Sci, Inst Mech, LHD, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 3.AI Sci Inst, Beijing 100080, Peoples R China |
| Recommended Citation GB/T 7714 | Zhang J,Guo TB,Dang GL,et al. Effects of wall temperature on hypersonic shock wave/turbulent boundary layer interactions[J]. JOURNAL OF FLUID MECHANICS,2024,990:35.Rp_Au:Li, Xinliang |
| APA | 张吉,郭同彪,党冠麟,&李新亮.(2024).Effects of wall temperature on hypersonic shock wave/turbulent boundary layer interactions.JOURNAL OF FLUID MECHANICS,990,35. |
| MLA | 张吉,et al."Effects of wall temperature on hypersonic shock wave/turbulent boundary layer interactions".JOURNAL OF FLUID MECHANICS 990(2024):35. |
| Files in This Item: | There are no files associated with this item. | |||||
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment