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| Gurney襟翼对翼型流场影响的数值模拟及研究 | |
| 引用本文： | 周铮,孙正中,申振华.Gurney襟翼对翼型流场影响的数值模拟及研究[J].燃气涡轮试验与研究,2010,23(2):19-22,9. |
| 作者姓名： | 周铮 孙正中 申振华 |
| 作者单位： | 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 |
| 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）Gumey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Gumey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Gumey襟翼的翼型获得了最高的升阻比。 |
| 关 键 词： | Gumey襟翼 翼型 数值模拟 |
Numerical Simulation and Research of the Effects of Gurney Flaps on Aerofoil Flow Field |
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| ZHOU Zheng,SUN Zheng-zhong,SHEN Zhen-hua.Numerical Simulation and Research of the Effects of Gurney Flaps on Aerofoil Flow Field[J].Gas Turbine Experiment and Research,2010,23(2):19-22,9. | |
| Authors: | ZHOU Zheng SUN Zheng-zhong SHEN Zhen-hua |
| Abstract: | The flow fields of NACA23012 aerofoil with four different height Gurney flaps(1%C,2%C,3%C,4%C) and the original aerofoil are numerically simulated,their aerodynamic performances,including Cl/Cd,pressure coefficient and Mach 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 Cl/Cd rises when Gurney flaps are attached to the aerofoil,and the lift force tend to distribute more reasonably.The high-est Cl/Cd... |
| Keywords: | Gurney flap aerofoil numerical simulation |
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