Turbojet is flying with a velocity of 100 m/s at a low altitude, where the ambient conditions are 1 MPa and 300 K. The pressure ratio across the compressor is 13, and the temperature at the turbine inlet is 1300 K. Assuming ideal operation for all components and constant specific heats for air at room temperature, determine
a. the pressure at the turbine exit,
b. the velocity and temperature of the exhaust gases,
c. the propulsive efficiency,
d. Using appropriate formula (NOT TABLE) to determine the Ma number at the exit of nozzle.