A small aircraft is powered by a single$-$spool turbojet engine with a convergent nozzle. It flies at a velocity $V_0=218\frac{m}{s}$ and at an altitude where the ambient pressure and temperature is $54$ kPa and $255$ K respectively. Using engine performance data given in Table Q$4$;

a$)$ Calculate the fuel mass flow rate.

$[9$ marks$]$

b$)$ Determine the engine thrust and thrust specific fuel consumption.

$\frac{5}{14}$

$\backslash$table$[[$Intake air mass flow rate,$66k\frac{g}{s}$

WILL GIVE GOOD REVIEW IF SOLVED CORRECT.