摘要
采用涡方法对静止圆柱绕流、简谐振动圆柱、静止NACA0012翼型绕流和运动扑翼的非定常流场进行了数值模拟和数值验证,对比验证结果较好。控制方程采用二维不可压缩N-S方程,根据算子分裂法,对流和扩散分别采用不同的时间步长。涡方法基于Lagrange坐标系的特点使其方便模拟运动物体的非定常流场。本文的工作为今后的翼型动态失速、运动翼型的塔影干涉效应、运动翼型的气动噪声研究等打下基础。
The unsteady flow field over static and harmonic oscillating circular cylinder,static NACA 0012 airfoil and flapping wing are numerically simulated by vortex method and numerically validated. Good agreements are observed.Controlling equation is two-dimensional incompressible N-S equation. According to the splitting-operator,different time steps are adopted separately for convection and diffusion.The feature of vortex method basing on Lagrange coordinate system makes it convenient to simulate the unsteady flow field of moving objects.And the work of present paper is the necessary base of the further numerical simulation of unsteady flow field of airfoil dynamic stall,the interference between moving airfoil and tower,aero-acoustics of moving airfoils.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2011年第3期407-410,共4页
Journal of Engineering Thermophysics
基金
国家自然科学基金重点项目(No.50836006)
国家自然科学基金青年科学基金项目(No.51006107)
