7. A turbofan engine is designed to operate at a flight Mach number of 0.80 and at an altitude where the ambient air temperature is 240 K. The core and bypass flows are mixed at constant pressure upstream of the mixed-flow condi-nozzle. The engine design parameters are summarised as follows: fan total pressure ratio 1.4 14 core compressor total pressure ratio turbine entry temperature 1400 K fan isentropic efficiency 90% core compressor isentropic efficiency 86% turbine isentropic efficiency 88% Calculate the following while ignoring all other losses and the fuel mass flow and take Cp (1000 J/kgK) and y (1.4) constant through the engine. a) the engine bypass ratio b) the specific thrust for the engine

7. A turbofan engine is designed to operate at a flight Mach number of 0.80 and at an altitude where the ambient air temperature is 240 K. The core and bypass flows are mixed at constant pressure upstream of the mixed-flow condi-nozzle. The engine design parameters are summarised as follows: fan total pressure ratio 1.4 14 core compressor total pressure ratio turbine entry temperature 1400 K fan isentropic efficiency 90% core compressor isentropic efficiency 86% turbine isentropic efficiency 88% Calculate the following while ignoring all other losses and the fuel mass flow and take Cp (1000 J/kgK) and y (1.4) constant through the engine. a) the engine bypass ratio b) the specific thrust for the engine