中文摘要：

本文采用URANS方法对NACA0012翼型在不同振荡方式下的非定常气动特性进行了数值模拟，并与实验和文献中DNS计算结果进行对比，结果显示：URANS方法较好地显示出翼型的俯仰振荡气动特性和近壁面速度随攻角变化规律，但未能模拟出前缘分离泡的生成和发展；对于沉浮振荡翼型，URANS方法能够模拟出尾涡的结构和尾涡间的相互作用。文中还对低频和高频振荡翼型的气动特性进行了分析。

英文摘要：

Numerical investigation of unsteady aerodynamic performance of NACA0012 airfoil under different oscillation modes is carried out by using URANS method. Compared with the experiments, it is seen that aerodynamic performance of the pitching oscillating airfoil and the variation of velocity near wall with attack angle could be well simulated. However, it is failed to show the leading edge separation bubble by URANS method. As for plunging oscillation, URANS method could simulate the wake vortex structure and the interaction of the wake vortices. The aerodynamic performance of the slow and fast plunging oscillating is also analyzed.