Grid fins are used in missiles and rockets effectively. The main drawback of grid fin is the higher drag compared to the convention’s fins. In this study, sweptback grid fin is analyzed using CFD and compared with the basic grid fin. Computations have been carried out at supersonic Mach numbers using HiFUN CFD software. The flow field around the basic and swept grid fins are analyzed and presented. The aerodynamic characteristics of the basic grid fin are compared with experimental data to validate the HiFUN software and found the comparison is good. The aerodynamic characteristics of the swept grid fin are compared with basic configuration. The results demonstrate decreases in drag coefficients for the sweptback fin compared to the basic fin at Mach numbers 1.8, 2.5, and 3.5, spanning different angles of attacks. Furthermore, slight increase in normal force and pitching moment coefficients are observed. Overall, these findings highlight the efficacy of the sweptback fin design in improving aerodynamic performance, suggesting potential enhancements in flight stability and efficiency under supersonic conditions.