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以求解二维N-S方程数值模拟NACA 0012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NACA 0012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。
In order to solve the two-dimensional N-S equation numerically simulating the flow characteristics of NACA 0012 airfoil at large angle of attack, the N-S equation is given in the body-fitted coordinate system and the C-type grid system is generated algebraically. In the LU-ADI format, 2nd and 4th order artifact terms were added to the implicit and explicit sections respectively to improve the stability of the format. The BaldwinLomax turbulent second-layer algebraic model was used to simulate the formation of vortex, vortex convection and unsteady flow at large angle of attack. The turbulent solution of the NACA 0012 airfoil at some Mach numbers and angles of attack has periodicity. By comparison, the numerical results in this paper are basically consistent with the corresponding numerical results of experiments and abroad.