O. AbstractThe next major aircraft program currently entering the study phase is to be a multi-mission fighter which would compliment the ATF and replace the F-16. The initial operational capability (IOC) of this aircraft will enable it to benefit from the propulsion technology advances of the Integrated High Performance Engine Technology (IHPTET) initiative. Past studies have shown that in order to achieve the optimum performance from these new advanced cores the engine cycle (specifically the fan pressure ratio) must be tailored to the aircraft mission and performance requirements.The missions and requirements to define this advanced fighter are currently in the embryonic stage. Even though the requirements are undefined, the engine company can evaluate a matrix of engine cycles in a notional airframe over a range of mission and performance levels. This effort can provide insight into the range of advanced engine cycles that might be required to optimize the future weapon system. This assessment can also provide a database to aid future aircraft designers, engine designers, and survivability analysts in their studies to recommend more specific requirements for this advanced multi-mission fighter.The focus of this paper is twofold. First, to present an approach which is used to generate a database of engine cycle/size as functions of mission definition and performance requirements. And second, to demonstrate how the aircraft mission and performance requirements impact the engine cycle and size. Specifically, a series of IHPTET class, Phase II, preliminary study engine cycles at four different fan pressure ratio (FPR) will be assessed in a notional advanced fighter performing four missions and at varied levels of performance requirements.