SpaceX Merlin Nozzle: Pt.2 - Running the Simulation | OpenFOAM tutorial 3
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- Опубліковано 2 жов 2024
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This is part 2 of a 3 part tutorial series where I will demonstrate how to perform a cfd simulation on a CD nozzle based on the specifications of a SpaceX Merlin. This simulation has been performed using the sonicFoam solver in OpenFoam.
In this part I cover how to run the case in OpenFOAM
I hope you enjoy the video. Please like, share and subscribe for more content.
Github: github.com/Int...
can axisymmetry be applied to save time and memory?
for sure. I am honestly considering re-doing this video at some point, likely with a 3d case as well.
@@interfluo6420 Thank you for putting this tutorial online. If I understand your setup correctly, you are performing a planar 2D simulation of a nozzle that is in reality axisymmetric. For a nozzle flow like that the change in cross sectional area is going to govern the expansion of the gas through the nozzle, which in this case you are not capturing as your geometry is planar, not axisymmetric. If you want to simulate a 2D axisymmetric flow you will need to use a CFD solver that solves the axisymmetric flow equations (or use the "wedge method" to achieve this in openFoam). Hope this helps. Cheers, Ragnar.
Thank you so much. I've learned too much things about OpenFoam from you. Thanks a lot again I'll follow you. Waiting for your OpenFoam videos impatiently.
Working on some now, I was just a bit busy with other things recently. Thanks for the comment!
hello , how can i download your case file ? i want to know other BC for p,T,k and .... can i have it?
Hello,
Thank you for making this great work.
I have some question about this project. How can I calculate epsilon (turbulence kinetic energy for this project)? Initially every where it was selected 266000.
When I run I get negative T0 error, How much should I decrease Delta T in order to avoid this error?
Thank you and Best Regards.
You can calculate k and epsilon at the inlet based on your turbulence model coefficients, average velocity and a given turbulence intensity. See the equations for k and epsilon.
I don't know what is going on about this T0 error. Are you setting T0 = 0?
What were your inlet conditions?
Thank you. But again why you are ignoring the bc step? How to compute the turbulence variable epsilon and k. For me that's the most important part in any simulation. Please don't get me wrong, you are wonderful because you are sharing this material. But please don't skip turbulence variables. It would be very nice to show how to compute them.
Thank you very much
I will dedicate an entire video to that in the near future.
Where is he ignoring the bc step? I think I miss that part, which part of the videos should I watch to see this ignoring?
@@samihupya4918 initial and boundary conditions for the velocity (U), pressure (p), epsilon etc.
@@interfluo6420 great
Case file worked great! Thanks for going into detail with the case setup :)
It is great to hear that it worked!
Dear Sir,
Thanks so much for this great example.
I’ve have a very basic question to ask. why are you using the compressible flow solver not incompressible, as far as i know the supersoinc flow should incompressible. could you plzz help me to answer this question? because this is my resarch now adays. i will wait for you answer
You have that flipped around; supersonic flow is compressible (think of density changes in a shock wave) and subsonic is incompressible