Flow field and aerodynamic characteristic of deflectable nose projectile at different angles of attack

Based on DES (detached eddy simulation) method and AUSM (advection upstream splitting method) scheme, the supersonic flow field and aerodynamic characteristic of deflectable nose projectile were simulated numerically at non-zero angle of attack and different deflectable angles. The results show that, at non-zero angle of attack, the shock wave on the windward of the projectile head with deflectable nose was much stronger than that of the normal one. When the effective angles of incidence of both projectiles were equal, the structures of flow field of head were all the same, and the flow field of tail fins were not affected by the deflectable angles even different angles of attack of projectiles. From the time history of aerodynamic force coefficients versus angle of attacks, it's found that the projectile with deflectable nose has good longitudinal static stability. Besides, the raising gradient of lift coefficient is much larger than that of drag coefficient, showing the lift-to-drag ratio is higher than normal projectile. Therefore, increasing the angle of attack properly can improve the aerodynamic characteristic of deflectable nose projectiles.