Gurney襟翼对单段翼型动态气动特性的影响  

Effect of Gurney flaps on aerodynamical characters of single airfoil

作　　者：周瑞兴[1] 惠增宏[1] 金承信[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,西安710072

出　　处：《流体力学实验与测量》2002年第2期30-35,共6页Experiments and Measurements in Fluid Mechanics

基　　金：国防科技预研基金资助项目(9515)

摘　　要：在西北工业大学NF 3风洞中对OA212MK旋翼翼型加装Gurney襟翼进行了静、动态的测压实验。研究了不同高度的Gurney襟翼在翼型后缘有、无平板(TAB)状态时的增升效果。实验结果表明,高度为0.010c的Gurney襟翼使OA212MK旋翼翼型的最大静态和动态升力系数分别增加了22%和16%,而使OA212MK+TAB的最大静态和动态升力系数分别增加了19%和5%。Effect of Gurney flap on OA212MK rotor airfoil was tested in NPU NF3 wind tunnel.The statical and dynamical pressure distribution were measured.In this paper,the results of lift increasement of different highness Gurney flap with and without table (TAB)at airfoil trailing edge are investigated.The experimental results indicate that for highness of Gurney flap 0.010c,the maximum statical and dynamical lift coefficient of OA212MK rotor airfoil increases 22% and 16%,the maximum statical and dynamical lift coefficient of OA212MK+TAB increases 19% and 5%,respectively.

关 键 词：GURNEY襟翼 单段翼型 动态气动特性 风洞 动态测压 升力特性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程] V211.41