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.