Hot combustion gases enter the nozzle of a turbojet engine at 260 kPa, 747°C, and 80 m/s and exit at 70 kPa and 500°C. Assuming the nozzle to be adiabatic and the surroundings to be at 20°C, determine
(a) The exit velocity and
(b) The decrease in the energy of the gases. Take k = 1.3 and cp = 1.15 kJ/kg €¢ °C for the combustion gases.

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260 kPa 747°C--+ 80 m/s Combustion gases 70kPa 500 C