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Several theoretical and empirical procedures are combined to form a useful design tool for computing static and dynamic aerodynamics on missiles, projectiles, and rockets. The Mach number and angle-of-attack range over which the method is applicable are O or = M or = 3 and O or = alpha or = 15 deg, respectively. Body and wing geometries can be quite general in that pointed or blunt nose bodies and sharp or blunt leading edge wings can be assumed. Computed results for several configurations compare well with experimental and other analytical results. The computer program is cost effective as it costs less than ten dollars per Mach number to compute the lift, drag, pitching moment, magnus moment, roll damping moment, and pitch damping moment of a typical wing-body shape on the CDC 6700 computer. Thus, a reasonably accurate dynamic stability analysis and performance estimates can be made for most tactical weapons up to Mach number 3 and angle of attack 15 deg without wind tunnel tests. Future efforts will be directed towards increasing the Mach number capability to 6, angle of attack to 180 deg, and incorporating air-breathing configurations into the analysis. (Author)