© 2014 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.The purpose of this study is to develop an accurate and efficient CFD code that can be used in hypersonic flows. The flow analysis is based on the three dimensional Navier-Stokes equations. These equations are solved by using Newton’s method. The analytical method is used to calculate the Jacobian matrix. Flow parameters and convective heat transfer are analyzed on Apollo AS-202 Command Module. Especially, temperature of nose and maximum temperature regions are observed. Assessment about general physics of flow is made to acquire some contribution to future studies.