【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。更多还原

【Abstract】 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.更多还原