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QUESTION 16 A turbofan engine is tested on a static aircraft on the ground in air at constant pressure specific heat capacity Cp = 1005 J-kg-1K-1 and absolute stagnation temperature To2 = 281 K. The fan draws in an axial inflow of velocity C1 = 148 m-s-1 as it rotates clockwise as seen from the front, with blade mid-span speed U = 203 m-s-1. The flow turns through the fan rotor blades by (B2-B1) = 31 degrees clockwise and the axial velocity component cx is constant. Evaluate the absolute stagnation temperature To2 at the rotor exit. State your answer in degrees Kelvin to zero decimal places and enter the numerical value only. Partial credit is awarded for a reasonable approximation to the correct numerical answer.