翼型大攻角绕流的数值模拟

 以求解二维N-S方程数值模拟NACA0012翼型大攻角状态的可压绕流特性;N-S方程是在贴体坐标系中给出的,以代数方法生成C型网格系统。采用LU-ADI格式计算,为提高格式的稳定性在隐式和显式部分分别添加了2阶和4阶人工粘性项。应用BaldwinLomax湍流二层代数模型模拟了大攻角时前缘分离涡的形成,旋涡对流及其非定常现象。在某些Mach数和攻角下NACA0012翼型的湍流解具有周期性。通过比较,本文数值计算结果同实验及国外相应的数值计算结果基本吻合。

THE NUMERICAL SIMULATION OF COMPRESSIBLE FLOW AROUND AN AIRFOIL AT HIGH ANGLE OF ATTACK

Compressible flow around an NACA 0012 airfoil at high angle of attack is numerically simulated by solving the two-dimensional Navier-Stokes equations in a body-fitted system, the grid system is C-type grid generated algebraically. The LU-ADI algorithm is employed in this paper, in order to control the numerical stability, the second-order and fourth-order artificial dissipation are added to the basic algorithm. By using the Baldwin-Lomax turbulent model, the formation of the leading edge separation bubble, as well as the convection of vortex along the airfoil surface and unsteady phenomena of vortex are simulated at high angle of attack. For some Mach numbers and angles of attack, the NACA 0012 airfoil turbulent solutions are periodie. By the comparison, the results in this paper agree with experiments and results received by other method.