Illustrative stationary thrust stand, not an identified engine. Chosen core airflow, fuel, temperature and pressure schedules; cp = 1150 J/(kg·K), gamma = 1.33, fuel heating value 43 MJ/kg, afterburner heat efficiency 85%, nozzle efficiency 90%, maximum afterburner total-pressure loss 5%. Ideal pressure-matched exit, inlet speed 0; exhaust mass includes both fuel streams. Throat area is relative to the dry core at the selected throttle. A teaching test-stand interlock closes all fuel unless the throat is within ±8% of its target; off-design nozzle thrust, ignition transients, compressor maps, wall cooling and real-engine limits are not simulated. Cutaway changes only inspection.