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This report contains numerical tables of aerodynamic coefficients and surface pressure distributions for sphere cone configurations as a function of angle of attack and Mach number. These results were generated by an NSWC/WOL computer code based on a finite difference solution of the steady inviscid three-dimensional compressible flow equation for a perfect gas deg = 1.4. Cone half angles of 5, 6, 7, 8, 9, 10, 15 and 20 are considered. Truncated values are obtained at axial stations to a length of 200 times the sphere radius, over a Mach number range of 3.5, 5, 10, 15, 20, 25 and 30, for an angle-of-attack span of 1, 3, 5, and 10 deg. Center-of-pressure location, and axial- and normal-force coefficients are tabularly presented at each axial-length increment station. Surface pressure distributions are also presented at each axial-length increment station, including seven meridian plane angles over the half plane from windward to leeward ray. The techniques utilized in generating the tables are described, and comparisons between computed values and values measured in some wind-tunnel experiments are presented. The presentation format is discussed to establish the mechanics necessary to use the tables. The tables are divided into two volumes; the first containing pressure information, and the second, aerodynamic information.