Aircraft Propulsion, Other Engineering




An aircraft is flying at a speed of 500 ft/s an altitude of 20,000 ft, where the atmospheric
temperature and pressure are 447.3°R and 972.5 lbf/ft2, respectively. If the inlet / diffuser
adiabatic efficiency is ?d = 0.92, compute the stagnation temperature and pressure at the
compressor face.



Rair = 1716 ft2/s2 –R cp,cold = 0.24 Btu/lbm-R cp,hot = 0.276 Btu/lbm-R cpAB = 0.29 Btu/lbm-R
?cold = 1.4 ?hot = 1.33 ?AB = 1.30
Posted Date: 4/8/2013 1:51:43 PM | Location : United States







Related Discussions:- Aircraft Propulsion, Assignment Help, Ask Question on Aircraft Propulsion, Get Answer, Expert's Help, Aircraft Propulsion Discussions

Write discussion on Aircraft Propulsion
Your posts are moderated
Related Questions
Is the dividend paid on common stock taxable to shareholders? The results paid on common inventory are taxed on two stages in the U.S. First at the company stage, as a results c


What is Trial Balance?  All business periodically tabulate the charge and credit worthiness stability separately in a declaration to see whether the complete of charge account b



simplify using k-map f=sum(0,4,5,6,9,10,12)+d(1,15)

i need to prepare my aasingment for financial data analysis for that i need 10 business events

Riveting  is a fixed fastening procedure in which the end of the metal pin is pressed over or spread out by hammering operation. Wrought iron and steel are used for the riveting an

what employment options are available in drafting

Oil tank: The oil tank is usually mounted on the engine; it may be a separate unit or part of an external gearbox called the sump. It has provision to allow the system to be f