Pressure Driven Supersonic Flow in Coverging-Diverging Nozzle (Wind Tunnel)
I have been trying to run this Mach 2.5 supersonic nozzle through OpenFoam and can't seem to figure out the correct boundary conditions. For reference, this is a nozzle that is attached to the 15cm x 15cm supersonic wind tunnel at NASA GRC.
Boundary conditions are:
After trying out a large number of combinations of boundary conditions (read as 50+), this following one seems to work the best: Pressure, p Code:
{ Temperature, T Code:
{ Velocity, U (changing the wall condition from slip to noSlip seems to not make a big difference with the centerline velocity) Code:
{ I get an outlet centerline velocity of around 630m/s or about Mach 1.83, which is definitely not correct. Do any of you guys have any suggestions as to what is wrong and why I am not getting Mach 2.5? Also, why do I have to use waveTransmissive instead of fixedValue for the outlet pressure? If I use fixedValue, I get a huge velocity discontinuity at the outlet. My case file exceeds the attachment limit, so I have, instead, put them in my Google Drive, accessible here: https://drive.google.com/open?id=1YQ...T9sU9mh8mpQw8h Thanks in advance for the help. I have been staring at this for the past 2 weeks, making little progress if any, albeit learning a lot about OpenFoam. |
Hi Shang,
why did you choose the value of lInf? What does it represent for you? What Solver are you using? I must be a compressible one. The waveTransmissive boundary condition is important to let pressure waves exit your CFD domain. Otherwise they get reflected and influence your solution. What is your progress? Lukas |
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