|September 3, 2012, 08:23||
help - Running Converging Diverging Nozzle with a shock wave
Join Date: Aug 2012
Posts: 9Rep Power: 5
I have recently started to work with fluent using the tutorial in the link:
They solved the nozzle problem for the case the flow is supersonic in all the nozzle with no shocks. I have succeeded to recapture their results.
Next I tried (independently) to solve the same geometry with a higher outlet static pressure to get (theoretically) a shock wave in the diverging section of the nozzle.
The total pressure at the inlet is atmospheric (101325 Pascal).
I tried to input several outlet pressure: 20,000 Pa, 30,000 Pa and such
and after running the program the solution didn't converge and I didn't get any good results (the residuals went up instead of down)
My question is, What could be the cause for this divergence?
As I said, theoretically, A shock wave should occur.
Does it require any special attention? setup settings or meshing.. etc.
Could it be that the divergence occurs due to a too coarse mesh?
(I was told that the mesh in the tutorial is quite coarse)
Thanks ahead ,
|Thread||Thread Starter||Forum||Replies||Last Post|
|about local bump shock wave drag reduction||fxzf||Main CFD Forum||5||February 26, 2010 13:04|
|Shock Wave||usker||STAR-CD||8||July 8, 2009 13:22|
|Shock in nozzle - dangerous?||Christian||Main CFD Forum||1||May 8, 2006 12:48|
|Shock Capturing in a Con-Di Nozzle.||Meriem Allouache||Main CFD Forum||3||December 27, 2004 06:49|
|Shock wave in Nozzle||Mohammad||Main CFD Forum||0||May 16, 2002 11:33|