The total pressures and temperatures of the gas are specified for a turbofan engine with separate exhaust streams (JT3D-3B from Pratt & Whitney, 1974). The mass flow rates in the engine core (or primary) and the engine fan are also specified for the sea level static operation. Calculate (a) the engine bypass ratio a defined as the ratio of fan-to-core flow rate (b) from the total temperature rise across the burner, estimate the fuel-to-air ratio and the fuel flow rate in lbm/h, assuming the fuel heating value is QR ~ 18,600 BTU/ Ibm and the specific heat at con- stant pressure is 0.24 and 0.26 BTU/Ibm - 'R at the entrance and exit of the burner, respectively (c) the engine static thrust based on the exhaust veloc- ities and the mass flow rates assuming perfectly expanded nozzles and compare your answer to the specified thrust of 18,000 lbs (d) the engine thermal efficiency