Aerodynamic prediction software is often used in the early stages of missile systems designed to quickly and accurately estimate the aerodynamics of a wide variety of missile configuration designs operating over many different flight regimes. It is also possible to use these empirical packages to validate flight data collected from wind tunnel tests and other open sources. Analysis of such data provides users with insights to the performance of a particular missile system and if necessary, enables the development of an appropriate defense system. Wind tunnel test data on an SA-2 class missile modified by suitable modeling was provided by MSIC. For this Thesis, this data set became the bench-mark for validating the Missile Datcom (97) empirical code that was used to compute the performance of the missile. The missile geometry was modeled using the interface MissileLab. A series of simulations for different flight operating conditions was carried out. The primary quantities compared were the axial force coefficient, CA and the skin friction coefficient, Cf. This Thesis describes the results obtained along with the geometry changes that became necessary to obtain reasonable agreement.