A turbojet aircraft flies with a velocity of $260$m$/$s at analtitude where the air is at $35$kpa and $-40\backslash$deg c$.$ Thecompressor has a pressure ratio of $10,$ and thetemperature of the gases at the turbine inlet is $1100\backslash$deg c Air enters the compressor at a rate of $45$kg$/$s $,$ and using variable specific heats $,$ determine $($a$)$ thetemperature and pressure of the gases at the turbineexit, $($b$)$ the velocity of the gases at the nozzle exit,and $($c$)$ the propulsive efficiency of the cycle