尾缘变弯对翼型气弹特性的影响分析

INFLUENCE OF TRAILING EDGE MORPHING ON AEROELASTIC

对于可进行尾缘变弯的二维翼型,研究其不同变弯形式对系统气弹特性的影响。研究基于数学建模方法,推导受控变弯翼型的气弹动力学方程,并建立相应的动态失速模型进行气动计算。对定常变弯、简谐变弯两种常见工况下系统的临界速度变化进行分析对比,发现定常变弯对气弹稳定性影响较小,简谐变弯的影响也可归纳为受迫振荡。在对结果的观察中发现反相的攻角-弯度角相位对振幅发散具有一定的抑制作用,据此进一步研究受控反相变弯下的气弹特性,发现一定的控制参数下确可抑制颤振出现,但也可能导致系统出现新的位移响应形式。

The influence of different morphing methods on aeroelasticity of trailing edge morphing airfoil was studied.Based on mathematical modeling method,the dynamic equation was derived and the corresponding dynamic stall model was built for aerodynamic calculation.Variation of critical velocity under steady morphing and harmonic morphing was studied,finding steady morphing only has minor aeroelastic influence and a harmonic morphing affects the system in the way of forced oscillation.Observation on the results indicates an opposite angle of attack-morphing angle phase can suppress the flutter to some extent.Then a further study regarding controlled opposite phase morphing is carried,finding under some control parameter the flutter can be refrained above the critical velocity,but may also leads to new kinds of aeroelastic response in other cases.