An Air Force jet has an engine under development that is being studied for performance capabilities while the aircraft is at an operating altitude of 2000m and at a velocity of 225 m/s. The gases leave the jest engine at the same lcoal pressure and a velocity of 600 m/s. The contribution of heat to the engine from combustion is 100kW. Neglect changes in potential energy and assume specific heats are constant through the process. Also neglect the contribution of products to the mass flow through the system.
a) Determine the pressure, temperature, and density of air at the operating altitude.
b) Determine mass flow rate through the engine [kg/s]?
c) Determine the exhaust temperature [C]?
d) Find the thrust produced by the engine [N]?