二维翼型跨音速绕流的数值模拟  

TWO DIMENSIONAL SIMULATION OF THE TRANSONIC FLOW OVER NACA 0012 AIRFOIL

作　　者：陈让福 

机构地区：[1]北京大学数学系

出　　处：《计算物理》1989年第3期277-288,共12页Chinese Journal of Computational Physics

摘　　要：本文结合高精度TVD格式的数值通量和时间进展多步法给出了一种求解定常流问题的数值方法。同时给出一些特殊处理来加快数值解的收敛速度。本文用以上方法计算了翼型跨音速绕流问题,结果表明此方法具有分辨率高,收敛速度较快之性质。A method which Combines the numerical flux of high accurate TVD scheme with multistage method in time approaching is developed to calculate the problems of 2-D steady flow. Some special treatments are given to accelerate convergency. The numerical results of transonic flow over NAG A 0012 airfoil are obtained by this method. They show that this method is high accurate, of high resolut- ion nd time-saving,

关 键 词：跨音速绕流 飞行器 数值模拟 翼型 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]