Numerical Simulation and Analysis of Aerodynamic Characteristics of an Oblique Tail Projectile
In this paper,the aerodynamic characteristics of an oblique tail projectile were numerically simulated u-sing CFD software.The partition grid method was adopted,and the Realizable k-εturbulence model was selected.The quasi time-invariant method based on moving reference frame model was used to solve the rotating flow field,and the aerodynamic characteristics of the projectile were obtained.The calculation results show that the drag coefficient,lift coefficient and pitching moment coefficient under roll condition are smaller than those under non-roll condition,but they are less affected by rotational speed,while the side force coefficient is just the opposite.In the rolling state,the drag coefficient,lift coefficient,pitching moment coefficient,steering moment coefficient and derivative of rolling damping moment coefficient,increase with the increase of the absolute value of the angle of attack,while the side force coefficient and rolling moment coefficient are less affected by the angle of attack.Though the comparison of ballistic analysis and measured results,it can be seen that the numerical simulation method of aerodynamic characteristics of the oblique tail projectile is reasonable and feasible,and has certain reference value.
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