An airplane flying at Mach 0.8 (P 1=80 kPa and T 1=230 K) with an inlet area of 1 m2 while exiting from a converging-diverging (C-D) nozzle with an exhaust area of 0.5 m 2 . It is known that the air/fuel ratio is 40 to 1 inside the combustion chamber and the exhaust gas has a density of 0.8 kg/m 3 , (a) determine the thrust developed by the engine if the exhaust gas has expanded to the ambient pressure P 5=P 1 at the exhaust outlet. (b) What is the stagnation pressure, P 04, before the exhaust flow entering the C-D nozzle if the jet nozzle efficiency ?j = 95%? Use ?=1.4, R=287 (J/(kg K), and C P =1,000 J/(kg K).