基于动网格技术的机翼动态失速仿真分析

Simulation Analysis of Wing Dynamic Stall Based on Dynamic Mesh Technology

为了研究机翼动态失速的演化机理,通过数学方程模拟动态失速状态下机翼摆动情况,对机翼表面涡量的变化规律进行了分析。首先基于动网格技术,结合机翼运动方程,模拟动态失速演化过程,利用Thin-cut技术生成机翼及其对应翼型的计算网格;然后将剪切应力传输(shear stress transfer,SST)k-ω模型与纳维尔-斯托克(Navier-Stokes,N-S)方程结合为封闭方程组用于翼型进行数值计算,并对计算模型进行了可行性分析;最后利用翼型计算时采用的方法对机翼动态失速过程进行数值求解。研究结果表明:在整个动态失速演化过程中,机翼动态失速气动力性能较翼型更为复杂,不同截面处具有不同的动态失速临界迎角,且存在着不同性质的涡旋变化。研究结果可为大迎角飞行安全训练提供支持。

In order to study the evolution mechanism of wing dynamic stall,a mathematical equation was used to simulate the wing swing under dynamic stall,and the variation law of wing surface vorticity was analyzed.Firstly,based on the dynamic grid technology and the wing motion equation,the dynamic stall evolution process was simulated,and the computational grid of the wing and its corresponding airfoil was generated by thin-cut technology.Secondly,shear stress transfer(SST)k-ωturbulence model and Navier-Stokes(N-S)equation are combined to form a closed system of equations for the numerical calculation of airfoil,and the feasibility of the calculation model was analyzed.Finally,the method used in the calculation of airfoil was used to solve the dynamic stall process of airfoil.The results show that the dynamic stall aerodynamic performance of the wing is more complex than that of the airfoil in the whole dynamic stall evolution process,and there are different critical angles of attack of dynamic stall at different sections,and there are different vortex changes of different properties.The results can provide support for safety flight training at high angles of attack.