Abstract: In order to investigate the aerodynamic characteristics of a canard missile with wraparound fins, steady-state and unsteady-state numerical simulations were conducted using the grid-centered finite volume method and slip-grid technique. The results show that the roll moments on the tail are not equal under the same roll deflection angle in opposite directions; under the same roll deflection angle,the positive deflection of the canard lets tail produces a larger anti-control moment than the negative deflection; when the deflection in same direction, the anti-control effectiveness decreases as the deflection angle increases. When the missile rotates, the Magnus force coefficient varies periodically with the roll angle. The fluctuation direction of the Magnus force is opposite for different rotation directions, and the Magnus force of reverse rotation is smaller than forward rotation. When the tail is rigidly coupled and rotating with the missile body, the Magnus force is mainly provided by the afterbody, and the Magnus forces on the fore and after bodies have opposite directions. When the tail is decoupled from the missile body, the Magnus force is smaller compared to the case of rigid coupling rotation. These conclusions can provide a basis for the design of missile control systems.