Sorry this may seem as if I am spamming this question.
Hello there, again I found a lot of questions regarding this topic but not a lot of them gave an answer towards the question, does anyone know how to fix this? I am currently working on a compressible steady state project on rocket nozzles, I’m trying to view the convergence and divergence airflow through the nozzle. Is there anyone that knows how to fix this, and does anyone have any suggestions to how I should approach making something like this?
If you’re curious on my project, you can view it here