In guided missiles, various surface configurations that can be represented as dimples or cavities, exist. This study investigates the impact of dimples applied to a blunt-fin configuration on drag and shock wave characteristics. Prior to conducting three-dimensional physical wind tunnel experiments, numerical analysis was performed on a two-dimensional model. The turbulence model employed for the numerical analysis was the SST K-W model, and numerical simulations were conducted in the Mach number range of 0.3 to 0.8. Dimple parameters, specifically depth and location, were systematically varied to compare drag coefficients and shock wave patterns. In this study, no significant drag reduction or changes in shock wave positioning due to dimples were observed in the subsonic regime. However, it was confirmed that dimples caused variations in shock wave positioning in the transonic regime, corresponding to Mach 0.8.