Abstract
A relatively simple equation set is developed to estimate the optimal performance of mixed-stream turbofans with component losses included. The set provides the specific fuel consumption and required bypass flow and fan pressure ratios to give a prescribed specific thrust for given flight conditions, component design limits, and engine core stream Mach number entering the mixer. Example results confirm the expectation (based on ideal cycle analysis) that the optimal specific fuel consumption and bypass ratio are nearly independent of the fan pressure ratio, provided that an optimal mixer is employed. Further, an engine designed for use in a mixedstream configuration only would best use a lower fan pressure ratio than would an engine deliberately designed for an unmixed exhaust. a0 ec ec> et F / G h K M m p pt S S3> T
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