Problem $04\mathrm{.}013-$ Calculate mass flow out exit of engine on a supersonic transport

A supersonic transport is flying at a velocity of $1508m\frac{i}{h}$ at a standard altitude of $50,000ft.$ The temperature at a point in the flow over

the wing is $793\mathrm{.}32.$ The total cross$-$sectional area of the inlet to the jet engines is $20f{t}^2.$ Assume that the flow properties of the air

entering the inlet are those of the free stream ahead of the airplane. Fuel is injected inside the engine at a rate of $0\mathrm{.}05$ lb of fuel for

every pound of air flowing through the engine $($i$.$e$.,$ the fuel$-$air ratio by mass is $0\mathrm{.}05).$ Calculate the mass flow $($in slugs$/$per second$)$ that

comes out the exit of the engine.

The mass flow is $87\mathrm{.}4$ slug$/$s$.$