Air enters the compressor of a gas turbine at 70°F and 0.8 psig and leaves the compressor at 300°F and 36 psig. It leaves the nozzle of the gas turbine at 650°F and 2.5 psig. With the atmospheric pressure of 14.7 psi and nozzle exit area of 4 in^2, determine the following:
a) Pressure ratio (2.5 points)
b) Ideal efficiency (2.5 points)
c) Thrust generated by the engine in lbf (10 points)
d) Mach number (5 points)