A normal shock is positioned in the diverging portion of a frictionless, adiabatic, converging-diverging airflow duct where the cross-sectional area is 0.1 ft2 and the local Mach number is 2.0. Upstream of the shock, p0 = 200 psia and T0 = 1200 R. If the duct exit area is 0.15 ft2, determine the exit area temperature and pressure and the duct mass flowrate.