A dual-shaft turbojet engine is cruising at a speed of M a = 2, and at an altitude with an ambient pressure of 11.0 kPa and an ambient temperature of 216.65 K. The overall pressure ratio across the two compressor sections is 11.3. Assume equal pressure ratios across the HP and LP compressors, all components have a polytropic efficiency of 90% and neglecting the fuel mass flow rate. Evaluate the stagnation pressure and temperature of the air entering this engine at these conditions.