| Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6 | |
Zhang J(张继)1,2; Guo TB(郭同彪)1; Dang GL(党冠麟)1,2; Li XL(李新亮)1,2
| |
| Corresponding Author | Li, Xinliang([email protected]) |
| Source Publication | PHYSICS OF FLUIDS
 |
| 2022-11-01 | |
| Volume | 34Issue:11Pages:15 |
| ISSN | 1070-6631 |
| Abstract | Swept compression ramps widely exist in supersonic/hypersonic vehicles and have become a typical standard model for studying three-dimensional (3D) shock wave/turbulent boundary layer interactions (STBLIs). In this paper, we conduct a direct numerical simulation of swept compression ramp STBLI with a 34 degrees compression angle and a 45 degrees sweep angle at Mach 6 using a heterogeneous parallel finite difference solver. Benefitting from the powerful computing performance of the graphics processing unit, the computational grid number exceeds 5 x 10(6) with the spatiotemporal evolution data of hypersonic 3D STBLI obtained. The results show that the flow of the hypersonic swept compression ramp follows the quasi-conical symmetry. A supersonic crossflow with helical motion appears in the interaction region, and its velocity increases along the spanwise direction. Fluids from the high-energy-density region pass through the bow shock at the head of the main shock and crash into the wall downstream of the reattachment, resulting in the peaks in skin friction and heat flux. The peak friction and heating increase along the spanwise direction because of the spanwise variation in the shock wave inclination. In the interaction region, the unsteadiness is dominated by the mid-frequency motion, whereas the low-frequency large-scale motion is nearly absent. Two reasons for the lack of low-frequency unsteadiness are given: (1) The separation shock is significantly weaker than the reattachment shock and main shock; and (2) because of the supersonic crossflow, the perturbations propagating at the sound speed are not self-sustaining but flow along the r-direction and toward the spanwise boundary. Published under an exclusive license by AIP Publishing. |
| DOI | 10.1063/5.0118578 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000880314400011 |
| WOS Keyword | LOW-FREQUENCY UNSTEADINESS ; FLOW ; SIMILARITY |
| WOS Research Area | Mechanics ; Physics |
| WOS Subject | Mechanics ; Physics, Fluids & Plasmas |
| Funding Project | National Key Research and Development Program of China ; National Natural Science Foundation of China ; [2019YFA0405300] ; [12232018] ; [91852203] ; [12072349] ; [12202457] ; [202202015832] |
| Funding Organization | National Key Research and Development Program of China ; 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/311007/90778 |
| 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 |
| Recommended Citation GB/T 7714 | Zhang J,Guo TB,Dang GL,et al. Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6[J]. PHYSICS OF FLUIDS,2022,34,11,:15.Rp_Au:Li, Xinliang |
| APA | 张继,郭同彪,党冠麟,&李新亮.(2022).Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6.PHYSICS OF FLUIDS,34(11),15. |
| MLA | 张继,et al."Direct numerical simulation of shock wave/turbulent boundary layer interaction in a swept compression ramp at Mach 6".PHYSICS OF FLUIDS 34.11(2022):15. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| Jp2022FA093_2022_Dir（6623KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment