Gurney襟翼对翼型流场影响的数值模拟及研究  

Numerical Simulation and Research of the Effects of Gurney Flaps on Aerofoil Flow Field

作　　者：周铮[1] 孙正中[2] 申振华[3] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]西北工业大学,陕西西安710072 [3]沈阳航空工业学院,辽宁沈阳110136

出　　处：《燃气涡轮试验与研究》2010年第2期19-22,9,共5页Gas Turbine Experiment and Research

摘　　要：本文采用计算流体力学的方法计算了NACA23012翼型以及安装四个不同高度(1%C、2%C、3%C、4%C)Gurney襟翼翼型的流场,并比较了不同来流马赫数、气流攻角条件下的气动性能,包括升阻比、翼型表面压力系数分布和马赫数分布。计算结果表明,安装Gurney襟翼后翼型的升阻比得到提高,升力分布趋于平均,在所计算的气流条件下安装3%C高度Gurney襟翼的翼型获得了最高的升阻比。The flow fields of NACA23012 aerofoil with four different height Gumey flaps （1%C, 2%C, 3%C, 4%C） and the original aerofoil are numerically simulated, their aerodynamic performances, including C/Cd, pressure coefficient and Math number distribution along both sides of the aerofoils, are further compared under various income flow Mach numbers and angles of attack. Results show that the CelC,t rises when Gurney flaps are attached to the aerofoil, and the lift force tend to distribute more reasonably. The highest C/Cd is got when the height of Gurney flap is 3%C.

关 键 词：Gumey襟翼 翼型 数值模拟 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程] V231.3