A static thrust stand for jet engine testing has an intake air velocity of 200 m/s and an exhaust gas velocity of 500 m/s. The intake area is 1.0 m2. At the inlet, the static pressure is 78.5 kPa and the static temperature is 286 K. The exhaust static pressure is 101 kPa. Assume an ideal gas with R = 0.2869 kJ/kg-K. Calculate the mass flow rate and the thrust of the engine.
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