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CHAPTER (12)

COMPRESSIBLE FLOW

SOLVED PROBLEMS

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SUMMARY1. Speed of Sound:

S

pc

kRTc

⎟⎟⎠

⎞⎜⎜⎝

⎛∂∂

=

=

ρ2

(Adiabatic Process)

4. Total Pressure:

⎟⎠⎞

⎜⎝⎛ −+= 2

211 MkTTt

2. Mach Number:

Isentropic Process (Adiabatic reversible)

3. Total Temperature:

5. Total Density:

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5. Kinetic Pressure:

6. Static Pressure Ratio across A Normal Shock Waves:

8. Mach Numbers Upstream & Downstream of a Normal Shock Waves:

7. Static Temperature Ratio across A Normal Shock Waves:

8. Mach Numbers Downstream of a Normal Shock Waves:

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9. Area Ratio in a Laval Nozzle:

10. Mass Flow Rate Through a Laval Nozzle:

11.

12. Critical Pressure Ratio :

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14. Variation of Mach No. with Pressure along a Pipe with Friction:

13. Mach No. Distribution along a Pipe with Friction

15. Mach No. Distribution along a Pipe with Friction for Isothermal:

16. Variation of Mach No. with Pressure for Isothermal Process :

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Problem (12.4)

Table (A-2),

Appendix (II)

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Problem (12.5)

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Problem (12.7)

CTGiven o30: 1 =

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Problem (12.7)

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Problem (12.12)

⎟⎠⎞

⎜⎝⎛ −+= 2

211 MkTTt

smVkPaPCTGiven

S

S

25020020:

=== o

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Problem (12.16)

FlowIsentropicsmVcmdkPaPCTGiven tt

250250020

====

,,: o

2

21Vhht += TCh P=

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Problem (12.16)

12

211

−

⎟⎠⎞

⎜⎝⎛ −+=

KK

t MkPP

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Problem (12.23)

31 =M kPaPCTUpstreamGiven

S

S

10020:

== o

Methane

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Problem (12.23)

CT o201 =

kPaP 1001 =

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Problem (12.28)

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Problem (12.36)

skgmCT

kPaPGiven

t

t

b

5550

30

==

==

&

o

:

Nitrogen

MPaP 1

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THE END