Use when you must compute the two-stream turbofan design point at flight Mach and altitude: traverse the fan-stream-station-states and the core stream of the separate-exhaust-cycle down the 0-2-13-2.5-3-4-4.5-5-9/19 station chain from the overall pressure ratio, the turbine-inlet temperature, the bypass ratio and the fan pressure ratio with the component efficiencies; close the two-spool-work-balance of the high-pressure compressor on the HP turbine and of the fan plus booster on the LP turbine; and report the burner fuel-air ratio, the per-stream nozzle exit velocities with the choked pressure terms, and the net thrust and TSFC of the separate-exhaust turbofan.
