双时间法求解大迎角翼型绕流非定常N-S方程  

Unsteady N-S Calculations Using a Dual-Time Stepping Methodfor Airfoils Oscillating at High Angle of Attack

作　　者：宋文萍[1] 杨永[1] 乔志德[1] Pahlke.K 

机构地区：[1]西北工业大学,西安710072 [2]德国宇航研究院

出　　处：《空气动力学学报》1999年第4期466-471,共6页Acta Aerodynamica Sinica

基　　金：德国教育;科学研究与技术部(收BMBF)资助

摘　　要：本文采用双时间推进法、顶点格式有限体积法求解非定常ＮＳ方程，应用多层网格技术计算了ＮＡＣＡ００１２ 翼型大迎角振荡绕流，并对伪时间推进收敛精度、物理时间步长、多层网格迭代方式等对计算结果与计算ＣＰＵ 时间的影响进行了讨论，另外还讨论了采用Ｂａｌｄｗ ｉｎ－ Ｌｏｍ ａｘ 湍流模型时用固定转捩或全湍流模式对计算结果的影响，并与实验结果进行了比较。A dual time stepping method is used to solve the unsteady two dimentional Navier Stokes equations for the unsteady motion of airfoils oscillating at high angle of attack. Results obtained from single grid and multigrid calculations are given and compared with the experimental data. The influence of the magnitude of physical time step, the inner iteration tolerance, the different multigrid strategy, the position of the transition points are also discussed. The efficiency of present method is increased a great deal compared to explicit methods.

关 键 词：双时间推进法 非定常NS方程 绕流 翼型 大迎角 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.41