Abstract: 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.