(a)
To compute: the pressure just downstream of this shock.
Answer to Problem 9.55P
Explanation of Solution
Given information:
Stagnation pressure is equal to
Throat area is
Shock is at
The pressure ratio is defined as,
Where,
Calculation:
Calculate the area ratio,
According to the table B.1 which represents the isentropic flow of perfect gas
By interpolation,
Calculate the pressure at point 1,
According to the table B.2 which represents the normal shock relations for a perfect gas,
By interpolation,
Therefore, the pressure
Conclusion:
The pressure just downstream of shock is equal to
(b)
To estimate:
Answer to Problem 9.55P
Explanation of Solution
Given information:
Stagnation pressure is equal to
Throat area is
Shock is at
The pressure ratio is defined as,
Where,
Calculation:
According to sub-part a,
We have found,
According to the table B.2 which represents the normal shock relations for a perfect gas,
By interpolation,
Therefore,
At
Therefore, calculate the relevant Mach number
According to table B.1
According to the table B.2 which represents the normal shock relations for a perfect gas,
By interpolation,
Therefore,
Calculate the pressure at point 3,
Conclusion:
The pressure at point 3 is equal to
(c)
To estimate: throat area.
Answer to Problem 9.55P
Explanation of Solution
Given information:
Stagnation pressure is equal to
Throat area is
Shock is at
According to sub-part a,
We have found,
Therefore, by using table B.2, we can find the relevant area ratio.
Calculation:
According to the table B.2 which represents the normal shock relations for a perfect gas,
By interpolation,
Therefore,
Conclusion:
The throat area is equal to
(d)
To estimate:
Answer to Problem 9.55P
Explanation of Solution
Given information:
Stagnation pressure is equal to
Throat area is
Shock is at
According to sub-part a,
We have found,
Therefore, by using table B.2 and B.1 we can able to estimate the Mach number at point 3
Calculation:
According to the table B.2 which represents the normal shock relations for a perfect gas,
By interpolation,
Therefore,
At
Therefore, calculate the relevant Mach number
According to table B.1
Conclusion:
The Mach number at point 3 is equal to
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Chapter 9 Solutions
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