摘要
本文采用LU-SSOR隐式推进方法,并结合TVD格式,计算了跨声速翼型的湍流解。文中采用Baldwin-Lomax模型,对NACA0012翼型给出了马赫数0.7~0.95的结果,并将部分计算结果与Harris的实验作了比较,二者符合较好。
A LU-SSOR method combined with TVD scheme is applied to compute the transonic airfoil flow in this paper, and the Baldwin-Lomax model is used. For NACA-0012 airfoil, we computed several different flow with an 161 × 41 'C' type grid by yaring Mach number from 0.7 to 0.95,and compared some of the results to the experimental data, good agreements were found. The results given in this paper show that the present scheme possess high accuracy for calculating transonic flow fields,and there is no any spurious oscillation near the shock wave.
出处
《空气动力学学报》
CSCD
北大核心
1996年第2期209-216,共8页
Acta Aerodynamica Sinica
基金
航空基金
关键词
TVD格式
激波
跨声速
机翼
NS方程
TVD scheme, shock kaye, LU-SSOR method, airfoil,NS equation, Baldwin-Lomax model.