Introduction to Flight 7th Edition by John Anderson

Exercise 3

Consider a turbojet mounted on a stationary test stand at sea level. The inlet and exit areas are the same, both equal to 0.45 m 2. The velocity, pressure, and temperature of the exhaust gas are 400 m/s, 1.0 atm, and 750 K. respectively. Calculate the static thrust of the engine. ( Note: Static thrust of a jet engine is the thrust produced when the engine has no forward motion.)