涡激振动小圆柱对翼型气动力影响的数值研究OA北大核心CSTPCD

Flow separation often occurs on the suction surface of an airfoil at a high angle of attack,deteriorating the aerodynamic performance of the airfoil.A control column is added at the leading edge of the airfoil to explore the influence of a small cylinder with vortex-induced vibration on the aerodynamic force of the airfoil through numer-ical simulation.Based on computational fluid dynamics,structural dynamics,and overset mesh technology,this study establishes a 2D-fluid-structure interaction model.Using the NACA0012 airfoil as an example,the flow field of the vortex-induced vibrating cylinder at the leading edge of the airfoil is simulated.The changes in the flow field between stationary and vibrating cylinders are then compared.The flow control mechanism of the small cylinder is analyzed using streamline and vorticity contours.The simulation results show that setting a stationary small cylinder can improve the lift-drag ratio of the airfoil at a high angle of attack.After the small cylinder produces vortex-in-duced vibration,it can further effectively improve the lift-drag ratio of the airfoil at a high angle of attack by more than 50%.The introduction of the vortex-induced vibration cylinder considerably enhances the lift-drag ratio of the airfoil at a high angle of attack.This effect implies that the established model is effective for controlling airflow and improving the aerodynamic performance of airfoils.