不同迎角的翼型气弹特性风洞实验研究

Aeroelastic characteristics of airfoils at different angels of attack in wind tunnel testing

基于可在不同迎角下作沉浮、俯仰两自由度运动的翼段振动装置,在低速风洞中分别针对普通薄翼型NA-CA0012和风力机翼型NREL S809进行气动弹性测试,得到不同实验状态的气动弹性振动时域响应。分别观察到经典颤振和失速颤振现象,并证明了迎角改变对两种翼型颤振特性的影响。

Based on the airfoil vibration model that can plunge and pitch at different angles of attack, the aeroelastic tests with typical airfoil NACA0012 and NREL S809 were implemented in the low speed wind tunnel, and sufficient vibration response in time domain with different wind speeds and angles of attack were measured. Via analyzing those aeroelastic responses under various experimental conditions, typical flutter and stall flutter were ob-served. It shows that the angle of attack effects on changes of the state of flutter.