Engineering, 05.05.2020 06:19 epicriderexe
Estimate the propulsion, thermal, and overall efficiencies of a turbojet engine during subsonic cruise. The flight Mach number is 0.8, and the ambient temperature is 225 K. The compressor pressure ratio is 12, and the turbine inlet temperature is 1300 K. The adiabatic efficiencies of the diffuser, compressor, turbine, and nozzle are 0.92, 0.85, 0.85 and 0.95, respectively. The combustor stagnation pressure ratio is 0.97, and the average specific heat during and after co
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Estimate the propulsion, thermal, and overall efficiencies of a turbojet engine during subsonic crui...
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