In order to meet the efficiency goals of the NASA generation N+3 aircraft, a new propulsive wing concept was developed and evaluated. High fidelity CFD simulations and inverse design methods were used to design a transonic airfoil section utilizing the Griffith/Goldschmied concept for increased laminar runs, reduced pressure drag, and wake filling. The design resulted in a 12.8% thick transonic airfoil section, which was developed for a Mach number of 0.7. This airfoil exhibits a reduction in drag of 62% (when suction is present) when compared to a next-generation commercial transport aircraft wing section at the design lift coefficient. A subsonic wind tunnel test was performed to validate the CFD methods utilized to design the airfoil. Cross-flow fans were investigated as the source of suction/blowing for the airfoil as they can be easily incorporated into a wing. Transonic testing of a cross-flow fan was also performed to investigate power requirements and suction capabilities of such a system. The results of these tests indicate that a cross-flow fan could be effectively used to provide suction and blowing in a transonic flow. Finally, a full aircraft systems analysis was performed to identify the change in fuel burn produced by implementing the propulsive wing concept on the Boeing SUGAR Refined aircraft, which was used as a baseline. Results indicate that a reduction in fuel burn of 11.8% can be achieved over the baseline case.