Gurney Flap绕流气动特性研究  

Navier-Stokes Analysis of Flow over Gurney Flap

作　　者：张振辉[1] 李栋[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家重点实验室,陕西西安710072

出　　处：《航空计算技术》2012年第2期32-35,共4页Aeronautical Computing Technique

基　　金：国家自然科学基金项目资助(11072200)

摘　　要：采用C-H型多块结构网格和SST k-ω湍流模型求解二维定常雷诺平均NS方程,对NACA4412单段翼型后缘附近和NACA63(2)-215B多段翼型襟翼后缘附近的Gurney Flap绕流进行了数值模拟。讨论了局部网格对计算结果的影响,重点研究了Gurney Flap位置和高度对气动特性的影响。计算结果表明:对于NACA4412单段翼型,Gurney Flap位置对气动性能的影响较小,但随着高度的增加,零升攻角和失速攻角减小,最大升力系数增大,同时阻力系数和力矩系数增加;对于NACA63(2)-215B多段翼型,Gurney Flap对气动性能的影响类似于NACA4412单段翼型情形。The flow over NACA4412 and NACA63（2）-215B with Gurney Flap was numerically investigated.This simulation employed 2D steady Reynolds-Averaged Navier-Stokes equations,which was solved with SST k-ω turbulence model on multi-block structure grid of C-H type.The influence of local grid on the numerical simulation was discussed,and the effect of the location and height of the Gurney Flap on the aerodynamic characteristics was mainly studied.The numerical results show that addition of Gurney Flap decreases the zero-lift and stall angle,and increases the lift coefficient and nose-down pitching moment but with drag penalty.

关 键 词：Gurney FLAP SST k-ω湍流模型 单段翼型 多段翼型 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]