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Calculate Gas Temperature at Exit of Turbojet Engine Method to Calculate the Gas Temperature at Exit of a Turbojet Engine 

Aerospace



Gas Temperature at Exit of a Turbojet Engine In order to calculate the gas temperature at the exit of the turbojet engine we assume that the airplane is flying at standard sealevel conditions. 

For calculating the gas temperature at exit we need,
The velocity at which the airplane is flying in ft/s Pressure Ratio across the compressor The fuel to air ratio by mass (default value is 0.05) Heat Released par pound of fuel. Default value is 1.4e7ft.lb/lbm Value of gamma = 1.4 and Value of the Gas constant = R = 1716 ft.lb/slug.R
Assumptions: The assumptions used in the calculation are, Air in the Diffuser is slowed to a velocity which is very low before entering the Compressor Nozzle exhausts the flow to ambient pressure.
Performing the calculation, the gas temperature at the exit of the Turbojet engine is computed. 

Download Free Program to Calculate the Gas Temperature at the exit of Turbojet Engine

