Consider the subsonic diffusor (inlet) shown below with M0 = 0.9, T0 = 222 K, P0 = 9570 N/m2. The mass flow rate of air through the engine is 100 kg/s. The upstream (external) deceleration is isentropic to the inlet face (i). The internal deceleration (from i to 2) is non-isentropic. Calculate the internal total pressure ratio (Pt2/Pti) and the static pressure entering the compressor if the Mach number entering the compressor is 0.4 and the area at station 2 (compressor face) is 3.99 m2