The nonlinear aeroelastic characteristics of a fighter-type wing with control surface have been investigated. The fictitious mass modal approach is used to reduce the problem size and the computation time in the linear and nonlinear flutter analyses. A Doublet-Hybrid method are used for the computation of subsonic unsteady aerodynamic forces. Structural nonlinearity of the control surface hinge is represented by a free-play spring. The linear and nonlinear flutter analyses indicate that the flapping mode of control surface and the hinge stiffness have significant effects on the flutter characteristics. The nonlinear flutter analysis shows that limit cycle oscillation and chaotic motion are observed in the wide range of air speed below the linear flutter boundary and the jump of limit cycle oscillation amplitude is observed. The nonlinear flutter characteristics and the nonlinear flutter boundary of limit cycle oscillation and chaotic motion have been investigated.

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