The reservoir pressure and temperature for a convergent-divergent nozzle are 5 atm and
The Mach Number
The exit pressure
The exit Temperature
The exit density
The velocity of flow at exit
The stagnation pressure at exit
The stagnation temperature at exit
Answer to Problem 10.1P
The Mach Number
The exit pressure
The exit Temperature
The exit density
The velocity of flow at exit
The stagnation pressure at exit
The stagnation temperature at exit
Explanation of Solution
Given:
The Reservoir pressure is
The Reservoir temperature is
The ratio of exit area to throat area is
Formula used:
The expression for calculating pressure is given as,
The expression for calculating temperature is given as,
The expression for density is given as,
Here,
The expression for velocity of sound is given as,
Here
The expression for speed of velocity is given as,
Calculation:
Refer to the “isentropic flow properties” for the Mach number at the ratio of exit area to throat area. The Mach number is obtained as,
Refer to the “isentropic flow properties” for the pressure ratio at the ratio of exit area to throat area. The pressure ratio is obtained as,
Refer to the “isentropic flow properties” for the temperature ratio at the ratio of exit area to throat area. The temperature ratio is obtained as,
The pressure at the exit is calculated as,
The stagnation pressure at the exit is calculated as,
The Temperature at the exit is calculated as,
The stagnation temperature at the exit is calculated as,
The Density at the exit is calculated as,
The value of gas constant is in English units is
The velocity at exit is calculated as,
The value of adiabatic constant is
Conclusion:
Therefore, The Mach Number
Therefore, The exit pressure
Therefore, The exit Temperature
Therefore, The exit density
Therefore, The velocity of flow at exit
Therefore, The stagnation pressure at exit
Therefore, The stagnation temperature at exit
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