ENGINEERING FUNDAMENTALS
ENGINEERING FUNDAMENTALS
6th Edition
ISBN: 9781337705011
Author: MOAVENI
Publisher: CENGAGE L
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Chapter 10, Problem 18P

Using the information given in Table 10.4, determine the ratio of local pressure and density to sea-level values. Estimate the value of air density at the cruising altitude of most commercial airliners.

Altitude (m) ρ ρ s e a l e v e l P P s e a l e v e l
0 (sea level)    
1000    
3000    
5000    
8000    
10,000    
12,000    
14,000    
15,000    
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Using the information given in Table 10.4 , determine the ratio of local pressure and density to sea-level values. Estimate the value of air density at the cruising altitude of most commercial airliners.
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The pressure in an automobile tire depends on the temperature of the air in the tire. When the air temperature is 25°C, the pressure gage reads 210 kPa. If the volume of the tire is 0.025 m3, determine the pressure rise in the tire when the air temperature in the tire rises to 60°C. Also, determine the amount of air that must be bled off to restore pressure to its original value at this temperature. Assume the atmospheric pressure to be 100 kPa. The gas constant of air is R = 0.287 kPa-m² ) = 0. 287 kPa m kg-K kg-K kJ 336 kPa. The pressure rise in the tire is The amount of air that must be bled off to restore pressure to its original value is 0.0070 kg.

Chapter 10 Solutions

ENGINEERING FUNDAMENTALS

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