Aerospace Engineering > GATE 2011 > Thrust Calculation
A turbojet powered aircraft is flying at Mach number 0.8 at an altitude of 10 km. The inlet and exit
areas of the engine are 0.7 m2 and 0.4 m2 respectively. The exhaust gases have velocity of 500 m/s
and pressure of 60 kPa. The free stream pressure, density and speed of sound are 26.5 kPa, 0.413
kg/m3 and 299.5 m/s respectively. The thrust of the engine (in kN) is
areas of the engine are 0.7 m2 and 0.4 m2 respectively. The exhaust gases have velocity of 500 m/s
and pressure of 60 kPa. The free stream pressure, density and speed of sound are 26.5 kPa, 0.413
kg/m3 and 299.5 m/s respectively. The thrust of the engine (in kN) is
Correct : 31.47
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