Air flows through a turbine airfoil passage in the shape of a converging-only nozzle with an exit cross-sectional area Ae=0.01 m2. The static back-pressure (or receiver pressure) is maintained at prec=100 kPa (absolute). For the conditions specified below, determine the exit Mach number (Me), exit velocity magnitude (Ve), exit static pressure (pe), and the mass flow rate (using the SI system). The inlet stagnation conditions are: 1. Tt1=500 K and pt1=150 kPa (absolute); 2. T=500 K and p=500 kPa (absolute).