Numerical simulation of separated flow around iced airfoil based on high⁃order schemes

被引：0
|
作者：
Nong L. [1 ]
Sheng Z. [2 ]
Xian J. [3 ]
Zhang H. [2 ]
机构：
[1] School of Systems Science and Engineering, Sun Yat⁃sen University, Guangzhou
[2] School of Aeronautics and Astronautics, Sun Yat⁃sen University, Guangzhou
[3] School of Mathematics, Sun Yat-sen University, Guangzhou
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷
关键词：
aerodynamics performence; high-order schemes; iced airfoil; Reynolds stress model; separation flow;
D O I：
10.7527/S1000-6893.2023.29291
中图分类号：
学科分类号：
摘要：
Computational Fluid Dynamics （CFD） is now widely used in aeronautics and astronautics as a crucial method of aircraft icing research. There exists deficiency in simulation accuracy and details capturing in the field of flow field structure or flow mechanism after icing and the change of aerodynamic characteristics. In this paper，numerical simulations of separated flow around three iced airfoils are conducted by using the SSG/LRR-g turbulence model equipped with the high-order discretization method WCNS，and compare with lower order accuracy schemes and different turbulence models. It is found that using the same turbulence model，the drag and pitching moment coefficient predicted by the WCNS are in better agreement with the experimental data than those predicted by the lower order scheme，and the error of the maximum lift coefficient predicted reduced. In addition，using the same accuracy scheme，pressure coefficient distribution at the surface，and the re-attached point of the separation bubble obtained by the current work are comparable to those of the experiment. © 2023 Chinese Society of Astronautics. All rights reserved.
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