Aerodynamic performance improvement of a blended wing-body re-entry vehicle using ANSYS CFX

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