To study the effect of Bang-Bang controlled canard on aerodynamic characteristics of the rotating projectile, the nested grid in CFD software was used to simulate the spinning of missile and the deflection of canard. By this method, aerodynamic characteristics of the Bang-Bang controlled rotating missile at different angles, Mach numbers and rotation speeds were numerically simulated, and the aerodynamic law of the rotating missile was obtained. The research shows that the immediate change of lateral forces will take place in projectile body and tail fin, due to the variation in canard washing current direction which coupled the missile spin. Compared with those without canard control, the periodic average lateral force coefficient under control decreases, while the normal force coefficient increases. Due to lateral force, the net force in a period deviates from the vertical direction, and the deviation angle of which decreases with the increase of Mach number, spin rate and attack angle.