A nonlinear aeroelastic analysis for a wing-box structure model has been conducted in the transonic and supersonic flow region. Transonic small disturbance code was incorporated into the analysis system to consider aerodynamic nonlinear effects. The fully coupled time-integration method (CTIM) was applied to observe the detailed aeroelastic responses considering the angle-of-attack and control surface deflection effects. The static aeroelastic computation has been conducted to obtain the converged deformed wing shape and initial aerodynamic loadings due to initial angle-of-attack and control surface deflection. Both vibration characteristics and nonlinear aeroelastic responses of the present wing model are presented in the subsonic, transonic and supersonic flow regime for several angle-of-attack and control surface deflection. Also, the computed flutter boundaries are presented and compared to show the effects of angle-of-attack and control surface deflection on transonic flutter stability.