In order to improve the firing accuracy of tail-wing projectiles, the rolling aerodynamic characteristics of high speed projectiles were studied. A simplified model of rocket projectile is established to simulate the rocket with different oblique blade angle of the rocket's wing. The finite volume method is used to discretize the space. The steady rotation of rocket projectile is simulated by multi-reference system model. The derivative of rolling damping moment and the balanced rotational speed of rocket projectile are obtained, and the aerodynamic characteristics of rocket with and without rotation are analyzed respectively. The calculation results show that the lift coefficient of rocket increases with the increase of angle of attack, but does not change with the increase of oblique angle of wing; the rolling damping moment derivative decreases sharply at high altitude, and the balance speed of projectile increases with increase of Mach number.