PS1_solution

# The more we speed the flow up the more the

This preview shows page 1. Sign up to view the full content.

This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: essure and density will decrease. PROBLEM 2d ( ) At the reservoir, ( ) ( This value is 11.5 % greater than ( ) ) calculated in part a. At the test section ( ) ( This value is 0.55% greater than The specific heat capacity ( ) ( ) ( ) ) calculated in part a. is 10.89% larger than the value ( ) . In general, the specific heat capacity of air increases with temperature. PROBLEM 2e At the reservoir, T= 900 K. From the given table, we have At the test section, T= 321.4 K. From the given table, we have after linear interpolation. We have the enthalpy relation, √( √( This value is 2.5% larger than ) ) calculated in part(b). PROBLEM 3a For an airliner flying at M=0.87: From Appendix E, for hg=35,000ft, () () () () To determine the stagnation temperatures, we assume adiabatic flow and use [ ( ) ( ( ) ) () () () () These numbers are far lower than that of the boiling point (100 C) of water at sea level and the maximum temperature (500F) of a typical home oven. PROBLEM 3b For a supersonic jet flying at M=2.0: From Appendix E, for hg=50,000 ft, () () (...
View Full Document

## This homework help was uploaded on 03/31/2014 for the course AAE 334 taught by Professor Collicott during the Spring '09 term at Purdue University.

Ask a homework question - tutors are online