摘要
本文针对采用振荡射流控制流动分离改善大攻角下翼型气动特性的问题,在NACA0015翼型上进行了多种工况的风洞实验。结果表明:在失速攻角附近,振荡射流抑制流动分离提高翼型升力系数的作用十分明显,可将翼型失速攻角推迟2°左右。存在最佳的振荡射流频率段、射流动量范围和射流位置,使得翼型性能的改善最大。实验还得到了振荡射流的频率、动量和施加位置等参数对翼型气动性能的影响规律。
In order to investigate airfoil aerodynamic performances improved by oscillating excitation at large attack angles, wind tunnel experiments with the airfoil of NACA0015 have been carried out under different conditions. The results indicate that the oscillating excitation has the effects of reducing flow separation and increasing airfoil lift when an inlet flow angle is near the stalling attack angle. At this time the stalling attack angle can be postponed about 2 degrees. There is an optimal frequency section, optimal momentum range and optimal injection positions of the oscillating excitation for getting the best airfoil performances. Some other characteristics of the influences of the oscillating excitation parameters on airfoil performances have also been found by the experiments.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2004年第5期765-768,共4页
Journal of Engineering Thermophysics
基金
国家重点基础研究专项经费资助(No.C1999022306)
关键词
振荡射流
流动分离控制
翼型
升力系数
oscillating excitation
flow separation control
airfoil
lift coefficient
