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The ability to predict the complete set of aerodynamic performance parameters for projectile configurations is the goal of the computational aerodynamicists at the U.S. Army Research Laboratory. To achieve this goal, predictive capabilities that use Navier-Stokes computational techniques have been developed and applied to an extensive number of projectile configurations. A summary of code validation efforts and applications for both spin-stabilized and fin-stabilized projectile configurations are described. Significant progress in the predictive capability for projectile aerodynamics has been achieved through the availability of substantial supercomputer resources and modern computational techniques. Current and future research areas of interest are described and provide an indication of computer resources and code enhancements needed to continue the progress in projectile computational aerodynamics. NomenclatureMagnus (side) force coefficient D =reference diameter of model, m d = local diameter of model, m / =mass injection parameter, / L =length, m M =Mach number m =mass flow rate of injected gas p/w/A, P =pressure normalized by p^2 (also spin rate, rad/s) PD/V =nondimensional spin rate Re = Reynolds number T = temperature, K u = velocity component in the x direction, m/s V =freestream velocity, m/s v = velocity component in the y direction, m/s x,y,z -Cartesian coordinates a = angle of attack, deg p = density, normalized by pĈ D = axial spin rate, rad/s