Answer: At an altitude of 11,000 m (a typical cruising

Chapter 18, Problem 21E

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QUESTION:

At an altitude of 11,000 m (a typical cruising altitude for a jet airliner), the air temperature is \(-56.5^{\circ} \mathrm{C}\) and the air density is 0.364 \(\mathrm{kg} / \mathrm{m}^{3}\). What is the pressure of the atmosphere at that altitude? (Note: The temperature at this altitude is not the same as at the surface of the earth, so the calculation of Example 18.4 in Section 18.1 doesn’t apply.)

Equation Transcription:

Text Transcription:

-56.5degC

kg/m^3

Questions & Answers

QUESTION:

At an altitude of 11,000 m (a typical cruising altitude for a jet airliner), the air temperature is \(-56.5^{\circ} \mathrm{C}\) and the air density is 0.364 \(\mathrm{kg} / \mathrm{m}^{3}\). What is the pressure of the atmosphere at that altitude? (Note: The temperature at this altitude is not the same as at the surface of the earth, so the calculation of Example 18.4 in Section 18.1 doesn’t apply.)

Equation Transcription:

Text Transcription:

-56.5degC

kg/m^3

ANSWER:

Solution 21E

To calculate the pressure of the atmosphere at the given altitude, we shall have to use the ideal gas equation , where P= pressure, V= volume, n= number of moles, R =gas constant and T= absolute temperature.

Given that,

Density

Molar mass of air

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