able $1$: Turbo$-$Prop Aircraft Data for use in Question $1$

Wing reference area $70$ m$2$

Mass $20000$kg

Maximum lift coefficient $($CLmax$)1\mathrm{.}8$

Drag polar$2$

D LC $0\mathrm{.}0250\mathrm{.}04$C$=+$

Propeller efficiency $92\%$

Specific fuel consumption $1\mathrm{.}0$x$10-7$ kg J$-1$

Ambient density at cruise altitude $0\mathrm{.}55$ kg m$-3$

Cruise speed $($TAS$)125$ m s$-1$Gross still$-$air range and endurance at cruise altitude and constant TAS$=125$ m$/$s$.$ The

initial total mass is $20000$kg$,$ of which $3000$kg is cruise fuel.