Question

A ramjet is to propel an aircraft at Mach 3 at high altitude where the ambient pressure is 8.5 kPaand the ambient temperature T-node is 220 K. The turbine inlet temperature T is 2540 K. If all components of the engine are ideal - that is, frictionless - determine (a) the thermal efficiency, (b) the propulsion efficiency, (c) the overall efficiency. Let the specific heat ratio be gamma = 1.4 and make the approximatios appropriate to f <<1.