The more we speed the flow up the more the

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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, () () (...
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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.

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