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Given conditions to a jet engine problem. (steady flow)
Rate of work = 2e7 J/s
Power generated by the turbing exactly equals this power required by the compressor.
Air enters at T=300K, P =0.1MPa, V=50m/s, mass flow rate = 40kg/s
Air leaved at P=0.12MPa, V=350m/s
Heat Transfer rate in combustion process is = 5e7J/s
a.) Find the enthalpy per unit mass at the exit of the engine.
b.) Find the temperature at the exit of the engine.
c.) Find the cross sectional aread of the engine intake.
What is the nozzle-exit-to-throat area ratio for case (a)? The gross thrust is the contribution to engine thrust made by the exhaust nozzle only.
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