求解平面翼型亚、跨声速绕流的一个新方法  

A New Method of Solution of Subsonic and Transonic Flows About Airfoils

作　　者：刘秋生[1] 濮存斌[1] 沈孟育[1] 王保国[1] 

机构地区：[1]清华大学

出　　处：《空气动力学学报》1996年第3期329-334,共6页Acta Aerodynamica Sinica

摘　　要：本文提出了求解平面翼型亚、跨声速绕流的一个新方法。引入流函数和ＶｏｎＭｉｓｅｓ变换后，亚、跨声速绕机翼无旋流动的基本方程组被化为以流线纵坐标ｙ为未知量的单个二阶偏微分方程──流线控制方程．并通过变换将物理平面上的无限域变为计算平面上有限的矩形域，而后在计算平面采用有限差分线松弛迭代法求解。作为算例，计算了对称翼型ＮＡＣＡ００１２－３４和非对称翼型ＮＡＣＡ４４１２的亚、跨声速有攻角绕流，所得数值结果与实验数据吻合良好。该法具有程序简单、大大节省内存和机时、收敛快等特点。A new method of solution of subsonic and transonic flows about airfoils is proposed in this paper. After the introduction of the stream function and von Mises transformation, the original equations of the flows are reduced into a single partial differential equation of order two,streamline governing equation. And the infinite solution region in the physical plane is transformed into a finite rectangular one in the computational plane. Then the equation is numerically solved by use of the finite difference method and line- relaxation iteration. The sub-and tran- sonic flows around airfoils NACA0012-34 and NACA4412 at an attack angle are calculated. The numerical results agree well with the experimental data. The numerical experiments show that the present method has advantages in simplicity, memory and CPU time saving and rapid convergence.

关 键 词：跨声速流动 位势流动 翼型 流线控制方程 

分 类 号：V211.412[航空宇航科学与技术—航空宇航推进理论与工程]