中文摘要：

通过求解雷诺平均Navier-Stokes方程得到气动力，结合翼型振动方程，计算了翼型不同迎角下的动态过程，分别通过层流和湍流情况的计算，重点研究了弹性振动对翼型失速迎角附近流场的影响，研究结果表明，在中低雷诺数、翼型具有弹性振动的情况下，翼型的失速迎角会比传统定常意义上的失速迎角提前出现，为长期以来数值计算得到的失速迎角与风洞实验、飞行试验结果的不同给出了一种物理解释。

英文摘要：

Based on the Reynolds-Averaged Navier-Stokes equations and the motion equations of an airfoil, the dynamic responses of the airfoil at different incidences are computed. Both laminar and turbulent flows are taken into account. The effects of elastic vibrations on the flow fields near the stall-incidence of the airfoil are investigated. It is shown that, under the elastic vibrations, the stall-incidence of the airfoil at low or middle Reynold number will appear earlier than that in the convention fully steady flow. This result may give an explanation for the fact that the differences of the stall-incidences always exist among the numerical, wind-tunnel, and flight test approaches.