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Pressure Inlet BC Inputs

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Old   October 29, 2021, 16:48
Question Pressure Inlet BC Inputs
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Kevin Davis
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I'm attempting to do a pressure inlet boundary condition for a supersonic oxygen inlet. The values given for the inlet are 914,468 Pa for stagnation pressure, 2.1 for mach number and 298 K for total temperature.

I was under the impression that stagnation pressure would be entered into "Gauge Total Pressure" and the "Supersonic/Initial Gauge Pressure" could then be calculated as static pressure using the isentropic flow relation, resulting in a value of 100,000 Pa. However, when I enter these values I end up with an initial velocity that is more than double what is expected for this oxygen jet. I am struggling to figure out what I am doing wrong and would greatly appreciate if anyone could provide any help. Thanks.
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Old   October 29, 2021, 19:52
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Lorenzo Galieti
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is the operating pressure set to zero?
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Old   October 29, 2021, 20:55
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Kevin Davis
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No it was not. This fixed my solution, thank you.
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pressure inlet, stagnation pressure, supersonic

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