A methodology for analyzing the boundary layer ingestion technology on a hybrid wing body aircraft has been developed using a simplified boundary layer analysis based on computation fluid dynamic results. With certain assumptions, a method for calculating the boundary layer velocity profiles across the flight envelope was shown using a log-wake velocity profile. This boundary layer profile was integrated over the surface of an assumed “D-shape” inlet to produce the inlet total pressure, temperature, and the ratio of the area averaged Mach number to the free-stream Mach number. The resulting curves were used within the EDS multi-disciplinary environment to analyze an HWB aircraft with BLI and other N+2 technologies over a range of cycle design parameters and for varying inlet aspect ratios. Aerothermodynamic engine cycle design explorations are performed that show that the candidate engine cycle selection that minimizes design mission fuel burn depends greatly on the assumed negative impacts BLI has on the engine performance.