DASSAULT MIRAG G is a two seat strike and reconnaissance fighter powered by one SNECMA TF$-306$C turbofaNumLock$0\mathrm{.}8$n engine. it has the following characteristics:

flight mach number $0\mathrm{.}8,$ altitude $65000$ft$,$ ambient temperature $216\mathrm{.}7$K$,$ ambient pressure $5\mathrm{.}5$kPa, fuel heating value $42700$ kJ$/$kg$.$ thrust force $53\mathrm{.}4$kN$,$ air mass flow rate $45$kg$/$s$.$ fuel mass flow rate $2\mathrm{.}5$kg$/$s$,$ aircraft gross weight $6(5000$ft$)$

DASSAULT MIRAGE $G$ is a two seat Strike and Reconnaissance fighter powered by one

SNECMA TF$-306$C turbofan engine. It has the following characteristics:

Flight Mach number $0\mathrm{.}8,$ Altitude $65,000$ ft$,$ Ambient temperature $216\mathrm{.}7K,$ Ambient pressure

$5\mathrm{.}5$kPa, Fuel heating value $42,700\frac{kJ}{kg},$ Thrust force $53\mathrm{.}4kN,$ Air mass flow rate $45\frac{kg}{s},$ Fuel mass flow rate $2\mathrm{.}5\frac{kg}{s},$ Aircraft gross weight$(65,000ft)156kN,$ Aircraft take$-$off weight $173\mathrm{.}3kN,$ Wing area $26\mathrm{.}4m^2,$ Fuel weight $5\mathrm{.}0kN,$ Maximum lift coefficient $C_L$max$=1\mathrm{.}8,C_{D0}=0\mathrm{.}012K_1=0\mathrm{.}2,K_2=0\mathrm{.}0,$ Air density at take$-$off $1\mathrm{.}225\frac{kg}{m^3},$ Air density at $650,000ft0\mathrm{.}88\frac{kg}{m^3}$

Assess:

i$)$ The specific thrust ii$)$ TSFC ii$)$ The exit velocity iv$)$ The thermal efficiency

The propulsive efficiency vi$)$ The overall efficiency vii$)$ The range factor