Air is flowing in a wind tunnel at 12^∘ C and 66 kPa at a velocity of 230 m / s. The Mach numbe

Name: Problem 154, Chapter 17: Thermodynamics: An Engineering Approach w/ Student Resources DVD
Uploaded: 2020-07-08T05:11:12-08:00
Duration: 1 min 43 s
Channel: Dading Chen
Description: Air is flowing in a wind tunnel at 12^∘ C and 66 kPa at a velocity of 230 m / s. The Mach number of the flow is (a) 0.54 m / s (b) 0.87 m / s (c) 3.3 m / s (d) 0.36 m / s (e) 0.68 m / s

step 1 Okay, so we know Mach number is equal to V over C, we know V is the air velocity, C is the speed

Question

Air is flowing in a wind tunnel at $12^{\circ} \mathrm{C}$ and $66 \mathrm{kPa}$ at a velocity of $230 \mathrm{~m} / \mathrm{s}$. The Mach number of the flow is (a) $0.54 \mathrm{~m} / \mathrm{s}$ (b) $0.87 \mathrm{~m} / \mathrm{s}$ (c) $3.3 \mathrm{~m} / \mathrm{s}$ (d) $0.36 \mathrm{~m} / \mathrm{s}$ (e) $0.68 \mathrm{~m} / \mathrm{s}$

   Air is flowing in a wind tunnel at $12^{\circ} \mathrm{C}$ and $66 \mathrm{kPa}$ at a velocity of $230 \mathrm{~m} / \mathrm{s}$. The Mach number of the flow is
(a) $0.54 \mathrm{~m} / \mathrm{s}$
(b) $0.87 \mathrm{~m} / \mathrm{s}$
(c) $3.3 \mathrm{~m} / \mathrm{s}$
(d) $0.36 \mathrm{~m} / \mathrm{s}$
(e) $0.68 \mathrm{~m} / \mathrm{s}$

Thermodynamics: An Engineering Approach w/ Student Resources DVD

Yunus A. Cengel,… 5th Edition

Chapter 17, Problem 154

Instant Answer

Solved by Expert Dading Chen

07/08/2020

Step 1

4 \times 287 \times (12 + 273)}\] where 1.4 is the specific heat ratio for air and 287 is the specific gas constant for air in $\mathrm{J} / (\mathrm{kg} \cdot \mathrm{K})$. Show more…

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Air is flowing in a wind tunnel at $12^{\circ} \mathrm{C}$ and $66 \mathrm{kPa}$ at a velocity of $230 \mathrm{~m} / \mathrm{s}$. The Mach number of the flow is (a) $0.54 \mathrm{~m} / \mathrm{s}$ (b) $0.87 \mathrm{~m} / \mathrm{s}$ (c) $3.3 \mathrm{~m} / \mathrm{s}$ (d) $0.36 \mathrm{~m} / \mathrm{s}$ (e) $0.68 \mathrm{~m} / \mathrm{s}$

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Key Concepts

Compressible Flow

Compressible flow theory deals with fluid flows where density variations are significant, typically at high velocities (high Mach numbers). Understanding compressible flow is crucial in aerodynamic applications such as wind tunnel testing, where effects of shock waves and expansion fans may need to be analyzed.

Mach Number

The Mach number is a dimensionless quantity representing the ratio of an object's speed to the speed of sound in the surrounding medium. It is a key parameter in characterizing compressible flows and determining whether a flow is subsonic, transonic, supersonic, or hypersonic.

Speed of Sound

The speed of sound is the rate at which pressure disturbances propagate through a medium, and it depends on the medium's thermodynamic properties such as temperature and gas composition. In air, it is influenced by factors like temperature and the specific heat ratio, which are essential for calculating the Mach number.

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