Abstract: To address the challenge of precise interception of low-slow-small targets such as unmanned aerial vehicles (UAV) in shipborne close-in defense, an investigation was conducted on the aerodynamic characteristics and trajectory correction performance of spoilers for 76 mm high-spin projectiles. CFD numerical simulation was adopted to obtain the additional aerodynamic coefficients of seven spoiler configurations, a 6-degree-of-freedom dynamic model considering aerodynamic additional forces was established, the correction effectiveness was quantified via the correction capability ellipse, and the ballistic stability and angle of attack characteristics were analyzed simultaneously. The results show that increasing the height and span of the spoiler significantly enhanced the additional aerodynamic coefficients, and the distance from the center of mass was more sensitive to the additional lift coefficient; its aerodynamic laws shared commonality with those of 155 mm projectiles in terms of consistent parameter influence trends, as well as differences due to scale effects; Configuration 7 achieved a correction radius of 450 m at a range of 5 km, making it suitable for maneuvering targets with a speed of 56.42 m/s. This study provides a theoretical basis and data support for the engineering design of spoilers for 76 mm projectiles and the ballistic control of close-in counter-UAV systems.