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
Answers: 2
Engineering, 04.07.2019 16:10
The force on a cutting tool are 2600n vertically downward and 2100 horizontal. determine the resultant force acting on the tool and the angle at which it acts.
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Engineering, 04.07.2019 18:10
Fluids at rest possess no flow energy. a)- true b)- false
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Engineering, 04.07.2019 18:10
Water at 55c flows across a flat plate whose surface temperature is held constant at 95c. if the temperature gradient at the plate's surface for a given value of x is 18 c/mm, find a) local heat transfer coefficient. b) heat flux
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Engineering, 04.07.2019 18:10
Carbon dioxide gas expands isotherm a turbine from 1 mpa, 500 k at 200 kpa. assuming the ideal gas model and neglecting the kinetic and potential energies, determine the change in entropy, heat transfer and work for each kilogram of co2.
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Estimate the propulsion, thermal, and overall efficiencies of a turbojet engine during subsonic crui...
Computers and Technology, 05.12.2019 22:31
Mathematics, 05.12.2019 22:31
Computers and Technology, 05.12.2019 22:31