Compare the specific fuel consumption of a turbojet and a ramjet that are being designed for flight at Ma = 2.0 and z = 10,000 m altitude. The turbojet compressor pressure ratio is 10 and the maximum allowable temperature in the Brayton cycle for this engine is 1,200 K. For the ramjet the maximum allowable temperature is 2,400 K. Conventional hydrocarbon fuels are to be used (heating value 44,000 kJ/kg). Assume k = 1.4. Which engine will be more efficient? How sensitive are your answers to the magnitude of the maximum allowable temperature?
We need at least 10 more requests to produce the solution.
0 / 10 have requested this problem solution
The more requests, the faster the answer.