Consider a simple turbojet engine with a compressor pressure ratio of $8,$ a TIT $1200$ K$,$ and a mass flow of $15$ kg$/$s$,$ when the aircraft is flying at $260$ m$/$s at an altitude of $7000$ m$.$ Assuming the following components, efficiencies, and I.S$.$A conditions, calculate the propelling nozzle area required, the net thrust developed, and the TSFC$.$ Isentropic efficiency of intake $0\mathrm{.}9$ Isentropic efficiency of compressor $0\mathrm{.}88$ Isentropic efficiency of turbine $0\mathrm{.}92$ Isentropic efficiency of propelling nozzle $0\mathrm{.}95$ Combustion chamber pressure loss is $6\%$ of compressor delivery pressure Combustion chamber efficiency $0\mathrm{.}98$ If the gases in the jet pipe are reheated to $2000$ K and the combustion chamber pressure loss is $3\%$ of the pressure at outlet from turbine, calculate The percentage increase in nozzle area required if the air mass flow is to be unchanged. The percentage increase in net thrust. $($Ta $=242\mathrm{.}7$ K$,$ Pa $=41\mathrm{.}06$ kPa, QR $=43,000$ kJ$/$kg$)$