This preview has intentionally blurred sections. Sign up to view the full version.View Full Document
Unformatted text preview: ASE 376K Homework # 4 Fall 2010 1. A preliminary design of an aircraft engine inlet is desired. The inlet is to supply 40 kg/s of air at M 2 = 0.45 to the compressor when the aircraft is cruising at M a = 0.87 at an altitude where ambient conditions are 26.5 kPa and 230 K . The diffuser adiabatic efficiency for the internal flow is 0.85 and 50% of the static pressure rise is to occur externally. Calculate the required inlet and exit areas A 1 and A 2 . 2. Air at an initial stagnation temperature and pressure of 400 K and 200 kPa is compressed to a final stagnation pressure of 1.50 MPa in a compressor with a constant polytropic efficiency η pc = 0.91. (i) Calculate the function T o ( s ) for this process and plot it on a T–s diagram. (ii) Calculate the final stagnation temperature, T oe . (iii) Calculate the adiabatic efficiency of the compressor η c , and check that η pc > η c . 3. Combustion products at an initial stagnation temperature and pressure of 1600 K and 800 kPa is expanded in a turbine to a final stagnation pressure of 250 kPa with an adiabatic efficiency η t = 0.93. Assume γ = 4/3, and R = 287 J/kg-K. (i) Calculate the final temperature, T oe ....
View Full Document
- Fall '10
- Fighter aircraft, Stagnation pressure, F-35 Lightning II, initial stagnation temperature, final stagnation pressure, constant polytropic efficiency