For the turbojet in 9.85, plot the velocity at the nozzle
Chapter 9, Problem 9.86(choose chapter or problem)
For the turbojet in Problem 9.85, plot the velocity at the nozzle exit, in m/s, the pressure at the turbine exit, in kPa, and the rate of heat input to the combustor, in kW, each as a function of compressor pressure ratio in the range of 6 to 14. Repeat for turbine inlet temperatures of 1200 K and 1000 K.
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