Abstract
In transonic region where a shock wave is staying on the aircraft wing surface, flutter often behaves like a limit cycle oscillation (LCO). It has been observed in the wind tunnel tests that the flutter controlled by a linear feedback also behaves as LCO. The authors have developed a nonlinear mathematical model, by the nonlinear dynamics approach, which can explain the fundamental bifurcation phenomena observed in the tests. Applying a linear feedback control to the nonlinear mathematical model, the paper shows that the bifurcation of LCO for the closed loop system can be analyzed and estimated by a continuation method
