Consider a nozzle with initial upstream entry pressure and temperature of thirty atmospheres and $4000R.$ The value of $=1\mathrm{.}2$ and the value of $c_p=\mathrm{.}30Bt\frac{u}{1}bmR.$ The throat area is $0\mathrm{.}75f{t}^2.$ The flow is perfectly expanded to the ambient pressure of $0\mathrm{.}70$ atmospheres. Calculate: $($a$)$ the mass flow, $($b$)$ the exhaust velocity, $($c$)$ the exit area, and $($d$)$ the thrust coefficient.