Abstract: In this paper, the aeroelastic stability of the laminated composite plate in subsonic airflow was analyzed.A subsonic aerodynamic model fit for the three-dimensional (3D) composite laminated plate was established by the linear potential flow theory.The equation of motion of the 3D composite laminated plate was obtained by Hamilton's principle and the classical laminated composite plate theory.The equation of motion was discretized to the ordinary differential equations by using the assumed mode method.The aeroelastic characteristics were analyzed by solving the generalized eigenvalue problem.The critical instability speeds of the laminated composite plate in subsonic airflow were obtained by calculating its natural frequencies at different flow velocities.The investigation results show that the subsonic aerodynamic model established in this paper is fit for the 3D plate structures.In subsonic airflow, the structural stiffness of the laminated plate is reduced, which results in the instability of the laminated plate structure.