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The increase in both computational capability (CPU speed, memory capacity, etc) and flow solver/grid generation sophistication over the last two decades has allowed for computational simulations of so-called "real-world" problems to become more commonplace. While not meant to suggest that new developments in computational science and simulation have reached their limit, it seems fair to say that the analogy of the computer being used as a computational or numerical wind tunnel has been, at least to some degree, realized. With regard to aero-propulsion applications, the computational simulation of engine components (inlets, nozzles, compressors, turbines, etc.) has been quite successful, especially over the past 10 -15 years. The topic of this paper is a qualitative demonstration of the scope that should logically follow component simulations, namely, that of simulating combined components on a system (or sub-system) level basis. While hypothetical in the sense that the actual hardware combination examined here does not exist, the results illustrate the interaction of the two components in the title and the importance of having the capability to conduct such system-level studies. Nomenclature AIP= aerodynamic interface plane A 0 /A c = ratio of free-stream flow area to inlet face capture area BWB = blended-wing-body CFL = Courant-Freidrich-Lax number

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