旋翼翼型动态失速特性的数值仿真研究  

Numerical Simulation Study on Dynamic Stall Characteristics of Rotor Airfoil

作　　者：邵明玉[1] 杨茂[1] 陈凤明[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2012年第7期70-74,共5页Computer Simulation

基　　金：国家自然基金项目(10872170);西北工业大学基础研究基金(G9KY1006)

摘　　要：旋翼翼型动态失速具有很强的非定常性与非线性,为研究动态失速发生时的气动和流场特性,基于CFD软件FLU-ENT,采用单方程S-A湍流模型,对NACA0012翼型的动态失速特性进行数值仿真。仿真结果显示,轻失速是后缘分离,旋涡影响范围小;深失速则形成了很强的前缘分离涡,结构复杂,影响范围大。参数研究显示,较大的湍流强度能减缓动态失速的发生,并且动态失速状态下的分离涡影响范围较小。通过与实验的对比证明,用S-A湍流模型的方法可以较好地仿真动态失速过程中旋涡的形成与发展过程。The aerodynamic and flow characteristics of rotor airfoil during dynamic stall were studied. Due to its highly unsteadiness and nonlinearity, dynamic stall characteristics of NACA 0012 airfoil were studied using CFD code, Fluent, with single equation S-A turbulence model. Results show that light stall occurs due to trailing-edge separation and vortex influenced region is relatively small; while strong leading-edge separation vortex, which has complex structure and large influencing region, is formed during deep stall process. Parametric study shows that high- er turbulence intensity can delay the onset of dynamic stall and reduce the affected region due to separation vortex. Validated with experimental data, present method is capable of simulating vortex formation and development during dynamic stall.

关 键 词：旋翼翼型 动态失速 计算流体动力学 湍流模型 湍流强度 

分 类 号：V448.253[航空宇航科学与技术—飞行器设计]