A. A. Luo - School of Mechatronic Engineering, Xi’an Technological University, Xi’an, Shaanxi, ۷۱۰۰۲۱, China
Q. K. Xiao - School of Mechatronic Engineering, Xi’an Technological University, Xi’an, Shaanxi, ۷۱۰۰۲۱, China
X. Liu - School of Electronic Information Engineering, Xi’an Technological University, Xi’an, Shaanxi, ۷۱۰۰۲۱, China
J. C. Guo - School of Opto-electronical Engineering, Xi’an Technological University, Xi’an, Shaanxi, ۷۱۰۰۲۱, China
Y. H. Zhang - School of Mechatronic Engineering, Xi’an Technological University, Xi’an, Shaanxi, ۷۱۰۰۲۱, China

A surface diversion groove with a specific geometry and position can influence the laminar flow characteristics of a projectile, which may affect the flight trajectory of an aircraft. The asymmetric flow field around the projectile can be induced by the diversion groove, which can produce an obvious aerodynamic force and moment at the projectile nose for trajectory correction. This study applied a diversion groove structure to the nose of tail-stabilized projectiles to investigate its impact on the aerodynamic characteristics of the projectile. The mathematical expressions for the aerodynamic force and aerodynamic coefficient were established theoretically. The change in the aerodynamic coefficient as a function of the phase angle of the diversion groove was determined. A parametric simulation was employed to investigate how the diversion groove affects the aerodynamic attributes of the projectile across various Mach numbers and angles of attack. The simulation results are consistent with the variation trends of aerodynamic forces and moments with respect to the phase angle of the diverter groove, as predicted by the static mathematical model. These findings demonstrate that the variation trends of the lift coefficient and pitching moment coefficient with respect to the angle β approximate a cosine function. Meanwhile, the variation trends of the yaw force coefficient and yaw moment coefficient with respect to the angle β approximate a sine function. The tail-stabilized projectile with asymmetrical diversion groove achieved a reduction of ۱.۲% in drag coefficient compared with that of the canard rudder corrective projectile, while the lift coefficient and pitch moment coefficient were increased by ۶.۴% and ۱۶%, respectively, in the subsonic regime. The static margin of the projectile ranging from ۱۳% to ۱۶%. This study offers valuable insights for the design of corrective structures with diversion grooves and trajectory control.

Diversion groove, Asymmetric nose, Two-dimensional correction, Ballistic correction projectile, CFD