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An experimental wind tunnel investigation and computational performance evaluation was conducted which focused on reducing the incremental drag resulting from external modifications to the fuselage of the AC- 130U Gunship. The objective of this effort was to establish a solid foundation via experimental and computational ground efforts to support flight test of drag reduction modifications to an aircraft. Currently, additive drag resulting from AC- 13 0U modifications decreases the range of the aircraft, increases the infrared heat signature of the engine exhaust due to the need for higher power settings, and has an adverse impact on takeoff and engine out performance. Specifically, the program consisted of six major thrusts: 1. Wind tunnel testing of a 1/48 scale model of the AC-130U fuselage to determine the drag on eight specific protuberances. 2. Design and testing of fairing modifications in 1/48 scale on three of the high drag protuberances. 3.