摘要
设计制作了两种布局形式的压电式合成射流致动器,采用热线风速仪在静止环境下对长方形喷口的速度场进行了测量,结果表明致动器喷口法向喷出最大速度可达到21.32 m/s.开展了基于合成射流技术的翼型分离流动主动控制实验,致动器采用倾斜喷出时速度为10 m/s量级,有效推迟了翼型表面流动的分离,改善了翼型的失速特性,最大升力系数提高11.36%,失速迎角增加3°.与此同时发现动量系数达到10-3量级时分离流动主动控制效果显著,动量系数小于10-4量级分离流动控制将几乎没有效果.
In order to carry out the experimental research on active control of separated flow over airfoils,two forms of synthetic jet actuators based on piezoelectric vibration diaphragm were designed.The hot wire anemometer measurements were performed on synthetic jets with rectangular orifice in quiescent environment.The results indicate that the vertical synthetic jets can obtain a maximum speed of 21.32 m/s.The airfoil separation active control experiment based on synthetic jet technology was performed in two-di...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第8期1759-1765,共7页
Journal of Aerospace Power
基金
国家自然科学基金(10802063)
关键词
合成射流
主动控制
致动器
失速
翼型实验
synthetic jet
active control
actuators
stall
airfoil experiment
