A converging-diverging nozzle operating at steady state has a throat area of
\(3 \mathrm{~cm}^{2}\) and an exit area of \(6 \mathrm{~cm}^{2}\). Air as an ideal
gas with \(k=1.4\) enters the nozzle at 8 bar, \(400 \mathrm{~K}\), and a Mach
number of \(0.2\), and flows isentropically throughout. If the nozzle is choked,
and the diverging portion acts as a supersonic nozzle, determine the mass flow
rate, in \(\mathrm{kg} / \mathrm{s}\), and the Mach number, pressure, in bar,
and temperature, in \(\mathrm{K}\), at the exit. Repeat if the diverging portion
acts as a supersonic diffuser.