Computational Fluid Dynamic of a Aerothermodynamics over a hot radiant blunt body the main objective of the project is to determine the pressure, velocity and temperature changes across the oblique shock wave over a wedge of angle at 14.23 an oblique shock wave is captured at Mach number 2 to read the temperature dependences, when an external energy is induced on it. The simulations are run to understand the pressure and temperature acting on the re-entry vehicle and to study the temperature dependencies on the oblique shock wave. The shock wave formed in the supersonic and hypersonic speeds are considered high-density air currents. So here we investigate what happens when temperature of the shock wave increases. To solve this we are using numerical methods like governing equation (continuity equation, momentum equation and energy equation) and ideal gas law equation. The geometry is modelled in the Design Modeller of ANSYS Workbench, meshing is carried out in Meshing tool of workbench and solving and post processing are carried out in FLUENT packages of ANSYS. The pressure and velocity differences are carried out in the three temperatures like 200 K, 300 K and 500 K. The velocity, pressure are dropped across the oblique shock wave depending on the surface temperature of the wedge, but the temperature rise across the shock is observed due to momentum change. There was no noticeable change occurred in the Mach number due to temperature change, this is because the heat transfer and radiation is turned off. Even if the heat transfer and radiation is turned on the solver encountered divergences in the solution and reported error without producing the results.