Table $1$: Cruise Data for Piston$-$Prop Aircraft

Number of engines & propellers $4$

Wing reference area $120$ m$2$

Total mass $30000$kg

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

Profile drag coefficientD$0$C $0\mathrm{.}025$

Maximum lift to drag ratio $12$

Propeller efficiency $92\%$

Specific fuel consumption $($s$.$f$.$c$.)1\mathrm{.}0$x$10-7$ kg J$-1$

Ambient density at cruise $0\mathrm{.}6$ kg m$-3$Estimate the total shaft power required to achieve a climb rate of $5$ m s$-1$ at a true

airspeed $10\%$ above VSTALL at ISA sea level conditions.