 
 Example 13.10 

 The temperature of the gases at the turbine exit is 1114.474397 K,
 The pressure of the gases at the turbine exit is 311.998817 kN/m^2,
 The velocity of gases at the nozzle exit is 1020.347840 m/sec,
 The propulsive efficiency of the cycle is 25.699731 percent 