A computational analysis of the external flowfield about a fighter configuration was conducted to evaluate an Euler solver and to investigate a hybrid combination of an Euler solver and a panel method. The analysis demonstrated the usefulness of Computational Fluid Dynamics (CFD) as a configuration design tool. The configuration selected for the study involved complex flowfields for which substantial wind tunnel test data were available. The Euler code provided good estimates for the incremental effects of aileron deflections using both wing-alone and wing-fuselage modeling.In general, the addition of the fuselage to the wing-alone model improves estimates of the effects of leading edge and trailing edge flap deflections. Using a hybrid combination of Euler code results with incremental effects of the tails from a subsonic panel method provides good estimates of trimmed drag changes for small flap/aileron deflections.