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For the design process of the class of aircraft known as an efficient supersonic air vehicle, particular attention must be paid to the propulsion system design as a whole including installation effects integrated into a vehicle performance model. The propulsion system assumed for the efficient supersonic air vehicle considered in this paper is a three-stream variable cycle engine. A computational model has been built with the Numerical Propulsion System Simulation (NPSS) software to analyze this engine. This engine model was based on the generic adaptive turbine engine model developed at the turbine engines division of the US Air Force Research Laboratory. Along with this variable cycle NPSS model, a three-ramp external compression inlet model meant for conceptual design has been developed. This model will be used to capture inlet installation effects, including those attributable to angle of attack changes at supersonic Mach numbers.