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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.
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.
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.
- Spring '09