摘要
在非结构自适应笛卡尔网格基础上构建了一种基于笛卡尔动网格的非定常气动力计算方法。为了适应非定常流场对网格品质要求较高的特点,网格生成采用了基于几何外形、模型表面曲率为基础的自适应生成及加密方法。采用显格式龙格库塔推进方法和中心格式空间离散的有限体积法对NACA0012翼型,三维机翼的跨音速刚性振动进行了数值模拟。对伪时间收敛精度控制,真实时间步长对结果的影响进行了讨论。将计算结果与试验数据进行了比较,得到了良好的效果。
A unsteady flow calculational method is developed in this article. This method is based on the Cartesian grid. The unsteady flow request a higher quality in grid so in this article the Cartesian grid is generated based on geometric and the body curvature. ALE equations are solved using the cell-centred finite volume method. An implicit dual-time method is used for the time advance. This is used to simulate pitching wing and airfoil. The influence of the magnitude of physical time step and inner iteration tolerance are discussed. The results of flow field computation are in agreement with the experiments.
出处
《航空计算技术》
2005年第2期24-28,共5页
Aeronautical Computing Technique
关键词
笛卡尔网格
有限体积法
双时间推进法
<Keyword>Cartesian grid
finite volume
dual-time stepping method
