$9\mathrm{.}4$ Consider a turbojet$-$powered airplane flying at a standard altitude of $40,000ft$ at a velocity of $530m\frac{i}{h}.$ The turbojet engine has inlet and exit areas of $13$ and $10$ ft $2,$ respectively. The velocity and pressure of the exhaust gas at the exit are $1500f\frac{t}{s}$ and $450l\frac{b}{f}t2,$ respectively. Calculate the thrust of the turbojet.