Concept explainers
The flow just upstream of a normal shock wave is given by
The downstream pressure.
The downstream temperature.
The downstream density.
The Mach number of downstream shock.
The pressure
The temperature
The entropy change.
Answer to Problem 8.7P
The downstream pressure is
The downstream temperature is
The downstream density is
The Mach number of downstream shock is
The pressure
The temperature
The entropy change is
Explanation of Solution
Given:
The upstream Mach number is
The upstream static pressure is
The upstream temperature is
Formula used:
The expression for the downstream pressure is given as,
Here,
The expression for the downstream temperature is given as,
The expression for the downstream Mach number is given as,
The expression for the downstream density is given as,
The expression for the pressure
The expression for the temperature
The expression for the entropy change is given as,
Here,
The expression for the pressure
Calculation:
The downstream pressure can be calculated as,
The downstream density can be calculated as,
Here, at pressure
The temperature of the downstream can be calculated as,
The Mach number at the downstream can be calculated as,
The pressure
The pressure
The temperature
The change in entropy can be calculated as,
Conclusion:
Therefore, the downstream pressure is
Therefore, the downstream temperature is
Therefore, the downstream density is
Therefore, the Mach number of downstream shock is
Therefore, the pressure
Therefore, the temperature
Therefore, the entropy change is
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Chapter 8 Solutions
FUND OF AERODYNAMICS(LLF) +CONNECT (1YR)
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