A blade pair in an axial flow compressor is being designed. The axial flow component of gas velocity is 183m/s. The engine diameter at the mean blade height is 0.83m and the blade height at rotor inlet is 0.16m. The rotor absolute inlet flow angle is 26 degrees. The stagnation conditions at the inlet to the blade pair are 297K and 132kN/m. Using Cp 1.005kJ/kg/K, R=0.287kJ/kg/K, and taking the ratio of specific heat capacities as 1.4, calculate the engine mass flow rate to the nearest kg/s.