As commercial airliners push for reduction in aircraft noise, emissions, and fuel burn, aircraft and engine manufacturers are accelerating the development of technologies aimed to meet those goals. A reduction in fuel burn, in particular, has led to a trend of very high bypass engines (VHBR), such as the PW1100G and the GEnx. By increasing bypass ratio (BPR) and the fan diameter, higher propulsive efficiencies for turbofans are able to be met, in turn decreasing TSFC. Engines with BPR greater than 25 are now deemed to be achievable through installing variable geometry, removing the nacelle-based thrust reverser, and installing the engine on next generation aircraft configurations. The objective of this work is to develop and investigate different aircraft and engine combination concepts that will provide a reduction in fuel burn. More specifically, a variable pitch geared fan with an aircraft-based thrust reverser, defined as VPF in this study, and a geared fan with a variable area nozzle and a nacelle-based thrust reverser, defined here as VHBR, will be compared on a tube and wing aircraft. To perform this study, each engine model will be implemented within the Environmental Design Space (EDS) in order to receive integrated, relative performance impacts of the two engines. A tradeoff study was then performed with a Boeing 737-800 to obtain the net vehicle fuel burn. EDS was modified to better quantify installation effects in order to meet constraints as fan diameter increases with BPR. Constraints for tire clearance, ground clearance, and roll angle were assessed and the engine location and/or landing gear length were updated accordingly. In order to counteract the new moment caused by the change in engine location, the vertical tail was then resized based on the new engine location. The analysis concluded that the VPF resulted in lower fuel burn than the VHBR when compared with the same engine parameters, and both engines needed to move outboard at lower fan pressure ratios (FPR) to maintain installation constraints.