$6\mathrm{.}25$: The following data apply to a twin$-$spool turbofan engine, with the fan driven by the LP turbine and the compressor by the HP turbine. Separate hot and cold nozzles are used:

$$ Overall pressure ratio: $20\mathrm{.}0$

$$ Fan pressure ratio: $1\mathrm{.}6$

$$ Bypass ratio: $3\mathrm{.}5$

$$ Turbine inlet temperature: $1300$ K

$$ Air mass flow: $120$ kg$/$s

$$ Find the sea$-$level static thrust and TSFC if the ambient pressure and temperature are $1$ bar and $288$ K$.$ Heat value of the fuel: $43$ MJ$/$kg