1) (20 pts) A high-bypass ratio (separate exhaust) turbofan engine powers a commercial transport. At the...

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1) (20 pts) A high-bypass ratio (separate exhaust) turbofan engine powers a commercial transport. At the cruise condition, the flight and engine operating conditions are: MM 0.88 TT=233 KK PP= 15 kkkkkk = 0.995 1.6 Cpc=1004 JJkkkkKK Q=42,000 kkkkkk ff 0.02755 Cpt=1152 JJkkkkKK ww ww ww mmmm = 0.95 BB= 8 = 40 T=0.95 T=0.95 TFF 0.95 YX = 1.4 = 0.992 YK= 1.33 mmmmmmmmhkkaaaammkkaa mmffffaammaammaammee Calculate: a. Total pressures and temperatures throughout the engine b. Nozzle exit static pressure (for both the core and bypass, checking if it is choked) c. Exhaust velocity of the fan and core (fluid velocity only) d. Effective exhaust velocity of the fan and core (this includes fluid velocity and pressure) e. Ratio of fan-to-core thrust f. Specific thrust of the engine based on total inlet flow, and Specific thrust based on core flow only g. Thrust specific fuel consumption (TSFC) h. All engine efficiencies: thermal, propulsive, and total d. Effective exhaust velocity of the fan and core (this includes fluid velocity and pressure) e. Ratio of fan-to-core thrust f. Specific thrust of the engine based on total inlet flow, and Specific thrust based on core flow only g. Thrust specific fuel consumption (TSFC) h. All engine efficiencies: thermal, propulsive, and total 2) (20 pts) Create a numerical algorithm (computer code) to do the calculations of Problem 1. Use the code to study the effect of bypass ratio on engine performance. Specifically, create plots showing (a) TSFC as a function of bypass ratio, (b) Specific thrust (both definitions) as a function of bypass ratio, and (c) all efficiencies as a function of bypass ratio, for bypass ratios from 0 (turbojet) to 10. Submit your code and the 3 plots. 1) (20 pts) A high-bypass ratio (separate exhaust) turbofan engine powers a commercial transport. At the cruise condition, the flight and engine operating conditions are: MM 0.88 TT=233 KK PP= 15 kkkkkk = 0.995 1.6 Cpc=1004 JJkkkkKK Q=42,000 kkkkkk ff 0.02755 Cpt=1152 JJkkkkKK ww ww ww mmmm = 0.95 BB= 8 = 40 T=0.95 T=0.95 TFF 0.95 YX = 1.4 = 0.992 YK= 1.33 mmmmmmmmhkkaaaammkkaa mmffffaammaammaammee Calculate: a. Total pressures and temperatures throughout the engine b. Nozzle exit static pressure (for both the core and bypass, checking if it is choked) c. Exhaust velocity of the fan and core (fluid velocity only) d. Effective exhaust velocity of the fan and core (this includes fluid velocity and pressure) e. Ratio of fan-to-core thrust f. Specific thrust of the engine based on total inlet flow, and Specific thrust based on core flow only g. Thrust specific fuel consumption (TSFC) h. All engine efficiencies: thermal, propulsive, and total d. Effective exhaust velocity of the fan and core (this includes fluid velocity and pressure) e. Ratio of fan-to-core thrust f. Specific thrust of the engine based on total inlet flow, and Specific thrust based on core flow only g. Thrust specific fuel consumption (TSFC) h. All engine efficiencies: thermal, propulsive, and total 2) (20 pts) Create a numerical algorithm (computer code) to do the calculations of Problem 1. Use the code to study the effect of bypass ratio on engine performance. Specifically, create plots showing (a) TSFC as a function of bypass ratio, (b) Specific thrust (both definitions) as a function of bypass ratio, and (c) all efficiencies as a function of bypass ratio, for bypass ratios from 0 (turbojet) to 10. Submit your code and the 3 plots.