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May 8, 2019, 06:27 |
Axisymmetric supersonic conical flow
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#1 |
New Member
Join Date: May 2019
Posts: 1
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Hi
I am trying to model the simple case of axisymmetric flow over a cone but I can't seem to get it to converge. My models are axisymmetric, ideal gas, coupled flow, spalart-allmaras turbulence. My mesh is: SimpleConeAxisymmetric_Mesh Scene 3.jpg The bottom is an axis, the left is velocity inlet, the right is pressure outlet and top is freestream. I have tried a lot of different models and meshes and nothing seems to work. If anyone has tips/advice I would appreciate it. Thanks in advance |
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May 8, 2019, 17:56 |
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#2 |
Senior Member
Matt
Join Date: Aug 2014
Posts: 947
Rep Power: 18 |
Have you tried mesh refinement to resolve the shock(s)? Just looking at your mesh, it looks like the steep gradients associated with the shock would not jive with the large cell size in the core flow (away from the body).
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May 10, 2019, 04:54 |
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#3 |
Super Moderator
Alex
Join Date: Jun 2012
Location: Germany
Posts: 3,427
Rep Power: 49 |
What you could try is using a ramp for the prescribed flow quantities at the boundaries. E.g. if you prescribe a velocity of 1000 m/s at the inlet then ramp it up over a few iterations. Define a field function like this and use it as the inlet velocity
Code:
((${Iteration} < 500) ? (${Iteration}/500.0) * 1000.0 : 1000.0 ) Btw: you probably don't need the mesh refinement at the boundaries left, top and right. What is your Mach number exactly? The mesh refinement region seems to be suitable only for very high Mach numbers, i.e. flows with a very narrow Mach cone. |
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October 16, 2019, 16:34 |
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#4 | |
New Member
P
Join Date: Mar 2019
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Quote:
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Tags |
axisymmetric, cone, conical, supersonic |
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