This study has been conducted to evaluate the merits and limitations of a subsonic and a supersonic analysis method used frequently in Government and Industry for predicting aerodynamic characteristics. Specifically the Unified Subsonic-Supersonic Aerodynamic Computer Program (USSAERO) was evaluation at Mach 0.4 for the subsonic case. The Supersonic-Hypersonic Arbitrary Body Program (HABP) was evaluated for the supersonic case beginning at a low Mach number of 1.50 and systematically increasing to Mach 4.63. Model geometries have been restricted to simple axisymmetric ogive forebody cylindrical afterbody combinations to aid in the relative comparison of the method capabilities. For the supersonic comparisons a data base was selected that featured a wide variety of nose bluntness and fineness ratios to determine their impact on the analysis capabilities. Specific limitations of the methods are identified from comparisons with detailed bodyt pressure coefficient data.