The stability and nonlinear vibration of a composite laminated plate in subsonic compressible airflow subjected to transverse harmonic external excitation are investigated.The linear potential flow theory is adopted to derive the aerodynamic model and the compressibility of the airflow is taken into account.The assumed mode method and Hamilton principle are used to obtain the nonlinear ordinary differential equation.The critical instability velocity and the flutter velocity are obtained by analyzing the natural frequencies of the linear system.