$2.$ It is desired to design a supersonic wind tunnel, operating in air $($ $=1\mathrm{.}40$; cp $=1004\mathrm{.}5$ J$/$kgK; R $=287$ J$/$kgK$)$ that produces a flow with Mach $4\mathrm{.}3$ in the tests and mass flow of $1$ kg$/$s$.$ Calculate the required pressure and temperature in the reservoir, as well as the throat and nozzle outlet areas $($The test section area corresponds to the nozzle outlet area$).$ Consider that the ambient conditions are $25$C and $1$ atm.