基于大涡模拟方法仿生翼型气动特性数值模拟

Numerical Simulation of Aerodynamic Characteristics of Bionic Airfoil Based on Large Eddy Simulation Method

采用大涡模拟方法,研究在翼型不同位置添加脊状结构对翼型流场及气动性能的影响。讨论了添加脊状结构后翼型流场的流动特性和涡结构特性。研究发现:(1)在α=6°攻角条件下,无论riblet-Q翼型模型或riblet-H翼型模型均可改善边界层分离情况,但riblet-H翼型模型表现出更好的控制效果;(2)后段布置脊状结构能够有效推迟翼型边界层分离点,抑制边界层大涡形成,控制分离涡的发展和脱落;(3)riblet-H翼型模型使翼型的升力系数增大,同时也使其阻力系数降低,升阻比较原翼型有了较大提高。

Large eddy simulation method was used to study the influence of groove structure at different positions on the flow and aerodynamic properties of airfoils.The flow characteristics and vortex structure characteristics of airfoil with groove structures were discussed.The results show these as follows:①at the angle ofα=6 degrees,both the riblet-Q model and the riblet-H model can improve the condition of boundary layer separation,but riblet-H model has better control effect;②the arrangement of groove structunres in the back section can effectively delay the separation of the boundary layer of the airfoil,restrain the formation of large eddy in the boundary layer,and control the development and shedding of the separated vortex;③The riblet-H model increases the lift coefficient of the airfoil,and also reduces the drag coefficient of the airfoil.Compared with the former airfoil,the lift-drag ratio increases greatly.