An aircraft is propelled by a reversible gas turbine engine, or turbojet. It is flying at an altitude of 30,000 ft where temperature is -20oF and pressure is 2000 psfa. The compressor has a pressurization ratio p2/p1 of 16 and the kerosene fuel in the combustion chamber delivers 30 Btu/lb. Make a drawing defining state points.
a) T, p, and h at all state points
b) Wd in every process
c) Heat transferred in every process
d) Net work and efficiency