(Solved): 40) 2. Calculate the static thrusts of the rocket and turbojet engines shown in the figure below. T ...

40) 2. Calculate the static thrusts of the rocket and turbojet engines shown in the figure below. The static thrust (script " $T$ " in the figures) is the force necessary to prevent horizontal movement of the engine. Both engines exhaust a mass flow of $120{\mathrm{lb}}_{\mathrm{m}}/\sec$. The ratio of air and fuel mass flowing into the turbojet is 50:1 and in the exhaust exit plane the velocity is $1500\mathrm{ft}/\sec$ and the pressure is the same as ambient pressure. The rocket contains all its own propellant and exhausts it at a velocity of $9000\mathrm{ft}/\sec$ through an area of $2{\mathrm{ft}}^2$. The pressure in the exhaust exit plane of the rocket is 22.5 psia and ambient pressure is 14.7 psia.