Calculate the propulsive efficiency and thrust for the Rolls & Royce engine

Olympus $593($see image$)$ at cruise conditions, given:

Alt $=51,000$ ft $($altitude$)$

M $=2($Mach number$)$

Vjet $=1009$ m$/$s $($jet velocity$)$

D $=1$ m $($inlet diameter$)$

Pa $=11\mathrm{.}0$ kPa $($ambient pressure$)$

Ta $=216\mathrm{.}7$ K $($ambient temperature$)$

Assumptions:

Air as ideal gas

mfuel smaller than m air so$,($mfuel $+$mair$)=$ mair