NUMERICAL ANALYSIS OF AERODYNAMIC CHARACTERISTICS OF CANARD WRAPAROUND FINS MISSILE

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 indicate that the roll moments on the tail are not equal when the same roll deflection angle is applied in opposite directions. Specifically, under the same roll deflection angle, a positive deflection of the canard generates a larger anti-control moment on the tail than a negative deflection. When the deflection are in same direction, the anti-control effectiveness decreases as the deflection angle increases. Additionally, as 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 during reverse rotation is smaller than during forward rotation. When the tail is rigidly coupled and rotating with the missile body, the Magnus force is primarily contributed by the afterbody, with the Magnus forces on the fore and after bodies having opposite directions. Conversely, 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 serve as a foundation for the design of missile control systems.