A turbojet engine powers an aircraft flying at a speed of 240 m/s, which has an exhaust speed of 760 m/s and a specific thrust of F/mₐ = 530 Ns/kg. The engine inlet area is A₁ = 0.6 m². Find the following:
a) Fuel-to-air ratio
b) Overall efficiency
c) Propulsive efficiency
d) Thermal efficiency
e) Thrust force