Consider an inviscid, adiabatic flow of air at free stream Mach Number, M_∞ = 2, across a compression corner (θ = 20°) as shown. The free stream total enthalpy is h_∞ = 810 kJ kg^–1. Assume that air is calorically perfect with γ = 1.4, R = 287 J kg^–1 K^–1. The total temperature at point P is