Numerical Study of Effects of Side-Wall Boundary Layer on Normal Shock Wave/Boundary Layer Interactions

被引：0
|
作者：
Wang Z.-Y. [1 ]
Tan H.-J. [1 ]
Zhang Y. [1 ]
机构：
[1] Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2022年 / 43卷 / 03期
关键词：
3D effect; Corner separation; Normal shock wave/boundary layer interaction; Side-wall boundary layer; Terminal shock;
D O I：
10.13675/j.cnki.tjjs.200491
中图分类号：
学科分类号：
摘要：
In order to investigate interactions between terminal shock wave of an external-compression inlet and boundary layers on the ramp and side-wall under critical condition, three simplified configurations with different side-wall lengths are specially designed to evaluate the effects of side-wall boundary layer thickness on normal shock wave/boundary layer interactions numerically. Simulation results show that the flowfield is quasi two-dimensional when there is no side-wall boundary involved in the interaction. However corner interaction structure is formed when side-wall boundary is involved in the interaction, and the increase of three-dimensional interaction structure in the corner leads to the suppression of quasi two-dimensional interaction structure in the symmetry plane. Besides, shock pattern transforms from quasi-two dimensional λ shock pattern into 'double λ shock + corner compression waves', which further makes reversal regions and topology of wall shear stress on the walls more complicated. © 2022, Editorial Department of Journal of Propulsion Technology. All right reserved.
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