Theoretical model of 2D curved shock wave/turbulent boundary layer interaction

被引：0
|
作者：
Cheng J. [1 ]
Shi C. [1 ]
Qu L. [2 ]
Xu Y. [2 ]
You Y. [1 ]
Zhu C. [1 ]
机构：
[1] School of Aerospace Engineering, Xiamen University, Xiamen
[2] Chinese Aeronautical Establishment, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2022年 / 43卷 / 09期
关键词：
curved shock; flow separation; flowfield structure; shock wave/boundary layer interaction; turbulent boundary layer;
D O I：
10.7527/S1000-6893.2021.25993
中图分类号：
学科分类号：
摘要：
With the wide application of curved compression configurations in internal/external flows, it presents a formidable challenge on perceiving shock wave/boundary layer interactions characterized by curvatures. Thus, to create new theories of Curved Shock Wave/turbulent Boundary Layer Interactions (CSWBLI) is of great importance. In this paper, an inviscid model of 2D incident curved shock wave/turbulent boundary layer interaction on a flat plate is built based on the curved shock theory and the free interaction theory. The flowfield is divided into three regions: the curved shock wave/expansion wave interaction region, the curved shock wave/separation shock interaction region and the boundary layer region, where the second order parameters behind the curved shock wave are used to describe the characteristics of the 2D CSWBLI flowfield. Thereafter, the accuracy of the model is verified by numerical simulations in five models with different Mach numbers and incident shocks, and the maximum error of the key point such as the separation point and the intersection point is less than 4.5%. Finally, the influences of incident shock, local boundary layer and downstream disturbance on the interaction are analyzed, and the rules of upstream influence length of the separation bubble in the 2D CSWBLI are summarized. The developed model is the fundamental of the flowfield structure of 3D CSWBLI, and also provides a new method for the research on CSWBLI in the future. © 2022 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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