A single$-$spool turbofan engine has the following data: Ambient temperature $288$ K Ambient pressure $101\mathrm{.}3$ kN$/$m$2$ BPR $($$)0\mathrm{.}7$ Overall pressure ratio $25$ Fan pressure ratio $3\mathrm{.}375$ Fuel heating value $($QR$)44,000$ kJ$/$kg Turbine inlet temperature $2000$ K Diffuser pressure recovery factor $($rd$)0\mathrm{.}9$ Compressor efficiency $($c$)0\mathrm{.}89$ Fan efficiency $($f $)0\mathrm{.}91$ Combustion efficiency $($b$)0\mathrm{.}98$ Burner pressure recovery factor $($rb$)0\mathrm{.}95$ Turbine efficiency $($t$)0\mathrm{.}98$ Nozzle efficiency $($n$)1\mathrm{.}0$ Flight Mach number $0\mathrm{.}3$ Calculate the thrust per unit mass flow rate and the TSFC$.$