翼型剖面绕流流场的CFD与势流数值模拟方法比较研究  

Comparative Study on Simulating Flow around Foil Section using CFD Approach and Potential Flow Theory

作　　者：程杰 方正 张伟 Cheng Jie;Fang Zheng;Zhang Wei(School of Ocean Engineering,Harbin Institute of Technology,Weihai 264209,China)

机构地区：[1]哈尔滨工业大学(威海)海洋工程学院,威海264209

出　　处：《水动力学研究与进展（A辑）》2023年第5期677-682,共6页Chinese Journal of Hydrodynamics

基　　金：海洋工程国家重点实验室(上海交通大学)开放基金(GKZD010081);船舶总体性能创新研究开放基金(14022103)。

摘　　要：该文采用计算流体力学CFD方法和基于势流理论的边界元方法,分别求解了二维翼型剖面NACA0015的绕流问题,其中CFD计算基于开源平台OpenFOAM开展,势流计算则采用自主开发的边界元程序实现。通过比较两种方法对不同攻角下翼型表面的压力系数、翼型总的升阻力系数以及翼型周围绕流速度场的预报结果,证明了在线性升力范围内,势流理论与CFD的预报结果相差并不显著,但在失速点之后,势流理论已经无法计算翼型的升力问题。Numerical simulations of the flow around a NACA0015 foil section are conducted, using a CFD approach and a potential flow theory based boundary element method. The CFD analysis are performed based on the open source platform OpenFOAM, while the potential flow computations are carried out by using a self-developed BEM code. Comparisons of pressure coefficients, lift coefficients, drag coefficients, and velocity field around the foil are made between the numerical results of two methods,demonstrating that both the CFD approach and the potential flow theory are able to evaluate accurately the performance of the foil under a low or moderate angle of attack. But potential flow theory cannot calculate the lift problem of a stalled foil.

关 键 词：势流理论 CFD 翼型剖面 绕流 NACA0015 

分 类 号：O352[理学—流体力学]