Air enters a frictionless, constant area duct with \(\mathrm{Ma}_{1}=2.0\), \(T_{0,1}=59^{\circ} \mathrm{F}\), and \(p_{0,1}=14.7 \mathrm{psia}\). The air is decelerated by heating until a normal shock wave occurs where the local Mach number is 1.5. Downstream of the normal shock, the subsonic flow is accelerated with heating until it chokes at the duct exit. Determine the static temperature and pressure, the stagnation temperature and pressure, and the fluid velocity at the duct entrance, just upstream and downstream of the normal shock, and at the duct exit. Sketch the temperature-entropy diagram for this flow.