Use matlab. Compute and plot the thrust specific fuel consumption $(TSFC)$ of a turbojet engine that has a

fuel mass flow rate of $0\mathrm{.}478k\frac{g}{s}$ and an air mass flow rate of $19k\frac{g}{s}$ over a flight velocity range

$0u_{a}300\frac{m}{s}.$ The exhaust velocity is of the fuel air mixture is $535\frac{m}{s}($and is subsonic$).$