only 5th question neededA gas generator for a turbojet engine with given maps for the compressor, turbine, and burner is to be assembled. The maps are shown in the following figures. The shaft mechanical efficiency is 0.995, the burner efficiency is 0.91, and the fuel has a heating value of 17,800 Btu/lbm. If the fuel ratio is 0.020, the corrected speed of the compressor is 9000 rpm, and the total temperature at the inlet to the compressor is 577°R, find the corrected compressor air mass flow rate, compressor total pressure ratio, and shaft speed. Show two complete iterations with an improving solution.Indicate the operating point on the figures.

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