This study investigates the flow field and aerodynamic characteristics of a two-dimensional trajectory correction projectile equipped with an actively controllable air-ducts structure suitable for spin-stabilized projectiles, using both numerical simulation and wind tunnel testing. The flow field structural characteristics of the projectile are analyzed under varying Mach numbers and angles of attack, and the effects of internal air duct geometric parameters on aerodynamic performance are examined. Wind tunnel experiments further validate the projectile’s radial correction capability under low-speed flight conditions. Key findings indicate that the lateral air jet generated by the oncoming airflow is smoothly discharged in both subsonic and supersonic regimes, and interactions between the lateral jet and oncoming flow at the duct outlet propagate downstream, altering the mid-to-rear flow field structure. The internal duct diameter directly affects aerodynamic forces: a 72% increase in diameter produces a 234.2% rise in lateral force under identical conditions. The outlet duct angle relative to the projectile axis strongly influences flight stability: a 13% increase in outlet duct angle θ reduces lateral force by 19% while increasing pitch moment by 15.1% and yawing moment by 37.5%. Minor axial displacements of the lateral outlet relative to the center of mass have negligible effects on overall aerodynamic performance. Experimental results confirm that the air-ducts structure provides measurable radial correction capability, demonstrating the effectiveness of the proposed aerodynamic modification scheme.
Cui et al. (Tue,) studied this question.