A developed fluid-structure coupling solver was used to study the aeroelastic response behaviors of curved panels subjected to an impinging oblique shock. The geometric nonlinear large deformation equations of curved panel were solved by finite difference method

while the fluid governing equations were solved by means of finite-volume scheme. The conventional serial staggered algorithm was adopted for the fluid-structure interaction. Numerical results demonstrated that as the dynamic pressure was smaller than the critical flutter dynamic pressure

the curved panel exhibited a static equilibrium state

and the asymmetry of the panel deformation was more pronounced with the increasing dynamic pressure. When the dynamic pressure was greater than the critical flutter dynamic pressure

the panel vibration displacement increased firstly and then decreased

and finally reached a stable flutter state. This limit cycle flutter was asymmetric about the initial point. Meanwhile

as the dynamic pressure increased

the maximum positive and negative displacements of panel flutter

and flutter amplitude increased gradually

but the frequency of flutter reduced gradually. The panel flutter behaviors did not monotonously increase or decrease with altering curvature of panel. The smaller initial curvature can reduce the critical dynamic pressure of panel flutter. However

as the panel curvature further increased

the quasi-periodic irregular oscillation was excited due to the enhancement of the aerodynamic nonlinearity

and the critical dynamic pressure rose rapidly.