Hypersonic missiles have been extensively being studied from 1900’s and are also being developed for multiple purposes, including reconnaissance, delivery of supplies, satellite launches, delivering conventional and nuclear payloads. Among the hypersonic missiles, hyper-ballistic missiles are the simplest type of hypersonic vehicle, that employ a ballistic trajectory to deliver one or more war heads to a predetermined target. This study presents a numerical simulation of a missile shaped body with fins using a Finite Volume based solver with the Reynolds averaged Naiver Stokes (RANS) based Spalart Allamaras (SA) turbulence model. The role of fins in enhancing the missile’s stability and overall aerodynamic performance is emphasized, demonstrating their critical contribution to the system’s effectiveness. The missile geometry taken for the computational study has blunt nose, a cylindrical body, and four symmetrically attached triangular shaped fins at the missile after body. The investigation focuses on the calculation of lift coefficient (CL), drag coefficient (CD), and Pitching moment coefficient (CM), at hypersonic speed considering the effect of Mach number of 5.75 and 8 for various angles of attack from 00 to 120, where the quality and quantitative results match well with the experimental data. Additionally, the simulation examines surface heat transfer rates on the missile body, where the simulations shows good prediction for such complex flows.