The present study deals with the aerodynamic data from the re-entry vehicle. The geometry of the re-entry vehicle is referenced from apollo crew descent module and soyuz crew descend module. The flow field of the re-entry phase is under hypersonic velocity, continuum air medium, with free stream conditions complying to the tropopause atmospheric layer of the earth. Mach numbers studied are 5 under 9000 pa atmospheric pressure. As the layer of atmosphere is tropopause the temperature remains constant (i.e.) 217 k. The methodology used here is computational fluid dynamics (cfd) using ansys fluent. To ensure the convergence of the solutions high speed numeric setting is enabled. The variables and properties studied here are contours of velocity, pressure, and velocity vector at various angle of attack such as 0°, 18° and 24° to the up-stream flow and the flow is along the axis of gravity. Based on these conditions and parameters, the results are obtained and compared and plotted for the investigative study.