Abstract: Roll damping derivative is an important aerodynamic parameter which affects the despinning effect of a missile. Steady CFD simulations are used to predict the roll damping characteristics of the missile with anti-rotation flaps at subsonic and transonic speeds. The predicted roll damping derivatives are in good agreement with the experimental data. The variation of the angle of attack and the surface pressure of wings due to rolling and the roll damping moment induced by additional wing lift are explained through numerical analysis. The bending location of the thin wings is shown. From the view of flow field, the influence of spinning on gas flow nearby the body of missile, the bending of surface streamline and the helical-like streamline pattern in the wake are demonstrated.

Key words: ordnance science and technology, roll damping derivative, missile body, anti-rotation flap, numerical simulation