The main objective of this paper is to evaluate the aerodynamic performance of a modified blended wing-bodied re-entry vehicle by computational fluid dynamics. This analysis examines the airflow properties like pressure, density, and temperature under hypersonic flow. The study of a blended wing model at different Mach speeds and angles of attack is also included in the research paper. All the simulations in this paper are performed using the computational fluid dynamics tool of ANSYS CFX. Shear stress transport (SST) turbulence computational fluid dynamics model has been used for numerical analysis. Various inlet conditions are applied to get the aerodynamic parameters. The results revealed that the best Re-entry condition is from 10 to 20 degrees angle of attack at Mach 22, and the vehicle is very stable at a high angle of attack and Mach number. The obtained results have been validated with the public domain literature. The blended wing body has been thoroughly examined in various important locations, particularly the spacecraft nose and flap sections.