(a)
To compute:
The pressure in the tank.
Answer to Problem 9.32P
Explanation of Solution
Given information:
The nozzle exit velocity is equal to
The stagnation temperature is defined as,
Where,
Speed of sound is defined as,
Where,
The Mach number is defined as,
Where,
The pressure ratio is defined as,
Where,
Calculation:
Convert,
Calculate the exit temperature,
Substitute for known values,
Therefore,
Calculate the Mach number at exit,
Calculate the pressure ratio,
In above equation,
Therefore,
Apply hydrostatic formula for above system,
Assume, the specific weight of mercury as,
Therefore,
According to equation 1 and 2,
The pressure inside the tank is equal to,
Conclusion:
The pressure inside the tank is equal to,
(b)
The atmospheric pressure.
Answer to Problem 9.32P
Explanation of Solution
Given information:
The nozzle exit velocity is equal to
The stagnation temperature is defined as,
Where,
Speed of sound is defined as,
Where,
The Mach number is defined as,
Where,
The pressure ratio is defined as,
Where,
Calculation:
Convert,
Calculate the exit temperature,
Substitute for known values,
Therefore,
Calculate the Mach number at exit,
Calculate the pressure ratio,
In the above equation,
Therefore,
Apply hydrostatic formula for the above system,
Assume, the specific weight of mercury as,
Therefore,
According to equation 1 and 2,
The atmospheric pressure is equal to,
Conclusion:
The atmospheric pressure is equal to,
(c)
To calculate:
The Mach number at exit.
Answer to Problem 9.32P
Explanation of Solution
Given information:
The nozzle exit velocity is equal to
The stagnation temperature is defined as,
Where,
Speed of sound is defined as,
Where,
The Mach number is defined as,
Where,
Calculation:
Convert,
Calculate the exit temperature,
Substitute for known values,
Therefore,
Calculate the Mach number at exit,
Conclusion:
The Mach number at exit is equal to
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