### 扩散界面浸入边界法结合壁面模型在湍流模拟中的应用

1. 1. 南京航空航天大学 航空学院 空气动力学系, 南京 210016;
2. 新加坡国立大学 机械工程系, 新加坡 117576
• 收稿日期:2021-09-01 修回日期:2021-09-14 发布日期:2021-10-09
• 通讯作者: 舒昌 E-mail:mpeshuc@nus.edu.sg
• 基金资助:
国家数值风洞项目（NNW2019ZT2-B28）；国家自然科学基金（11772157）；江苏高校优势学科建设工程资助项目（PAPD）

### Wall model based diffuse-interface immersed boundary method and its application in turbulent flows

DU Yinjie1, SHU Chang2, YANG Liming1, WANG Yan1, WU Jie1

1. 1. Department of Aerodynamics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Department of Mechanical Engineering, National University of Singapore, Singapore 117576, Singapore
• Received:2021-09-01 Revised:2021-09-14 Published:2021-10-09
• Supported by:
National Numerical Windtunnel Project (NNW2019ZT2-B28); National Natural Science Foundation of China (11772157); Priority Academic Program Development of Jiangsu Higher Education Institutions (PAPD)

Abstract: A diffuse-interface Immersed Boundary Method (IBM) for simulating high Reynolds number turbulent flows is proposed. This method uses the wall model to reduce the number of grids near the wall. To implement the wall model and boundary conditions, two auxiliary layers (a series of Lagrangian points) are set outside the wall: the outer reference layer carries out the wall model to calculate the wall shear stress, and the inner enforced layer implements boundary conditions off the wall. When the wall model is implemented, the momentum equation is integrated along the normal direction of the wall, such that the tangential velocity correction is related to the wall shear stress obtained by the wall model, and the normal component of the velocity is approximately reconstructed according to the parabolic distribution. Furthermore, when implementing boundary conditions, we adopt the implicit velocity correction-based IBM to satisfy the non-penetration condition. Finally, the feasibility of this method is verified by numerical simulation of the turbulent flows around the flat plate and the NACA0012 airfoil.