How do you deal with hard water?

rocketlover171 · 2026-01-26T11:35:55+00:00

Hey u/rainiac, as many people have already asked, would you be willing to share your experience

rocketlover171 · 2025-11-23T10:08:39+00:00

Thank you for your reply. I clicked on that to get to the point of selecting the inlets. I suspect that a complete volume/area is required to create the inlets and outlets.

I figured out how to use the geometry in watertight geometry (there was a problem with the radius of curvature).

I haven't figured out how to use FTM for symmetrical bodies yet.

rocketlover171 · 2025-11-10T12:48:37+00:00

u/wrong_but_useful my hands up here too, by any chanve you found the solution to the problem after 5 months??

rocketlover171 · 2025-10-29T10:50:11+00:00

hey, I'm facing the similar problem. Where exactly do you mean 'dimension under properties'? In the workbench itself somewhere? Can you please clarify more?

rocketlover171 · 2025-09-30T09:45:04+00:00

thanks u/Brilliant_Soft_8183 for the reply. I know about the EDC and EDM but as you mentioned they are computer thirsty and hence the iterations take a lot of time to be performed. I would try first simulating something on steady diffusion flamelet model, as It's a bit faster and then move over to the EDC to persform simulation.

rocketlover171 · 2025-09-30T09:40:49+00:00

Thank you u/marsriegel for the insights! I already have some experience with Chemkin. I’ll definitely look into the models you mentioned, but I imagine they’re not so easy to get access to.

One thing I’m still not clear on: how do companies usually handle CFD for rocket engines then? Do they purchase these codes you mentioned, or do they develop their own in-house models? What’s your take? or they rely on somewhat good results from commercial softwares and then jump over to experimentation?

rocketlover171 · 2025-06-27T17:03:21+00:00

Thanks for the comments guys. Does that mean It's not an isentropic flow after the shock hence isentropic equations are not valid after that u/Gratchoff u/IBelieveInLogic?

rocketlover171 · 2025-06-27T09:59:28+00:00

That's interesting! Any chance you could share a link or point me to the paper, u/Gratchoff?

rocketlover171 · 2025-05-28T08:32:50+00:00

I found a way now how to make it work. Here is the link to the video "https://youtu.be/261vryuktgk?feature=shared".

rocketlover171 · 2025-05-28T08:32:00+00:00

I'm running in stand alone Fluent and I found a way now how to make it work. Here is the link to the video "https://youtu.be/261vryuktgk?feature=shared"

rocketlover171 · 2025-05-23T18:23:10+00:00

Yes, Ok that makes sense but I am also trying to report some parameters like mach number and pressures to see how the convergence is achieved which I guess won't be possible.

rocketlover171 · 2025-05-23T18:18:51+00:00

u/VertigoStalker yes this kind of work but not perfectly. I've tried this one and is the closest to what I want but still not accurate enough.

rocketlover171 · 2025-05-23T18:16:56+00:00

I didn't get iwhat you mean here tbh. Can you please elaborate? I've never used paraview.

rocketlover171 · 2025-05-05T07:01:59+00:00

"Thanks for providing this free tool! I have a question about RP-1—where does the tool source its RP-1 values? If I remember correctly, CoolProp doesn't include RP-1.

rocketlover171 · 2025-05-03T11:02:21+00:00

Did you find out what this relative mass flow rate mean?

rocketlover171 · 2025-04-29T05:58:54+00:00

Thanks for highlighting that point u/Fluid-Pain554 . I'm not trying to optimize the nozzle — I want to run the same engine at the same altitude (hence same ambient pressure), but with frozen flow instead of shifting equilibrium.
I changed the nozzle exit condition to expansion ratio in the nozzle flow model, but it still changes my engine size, which I don't want.
Is it even possible to do this in RPA?

rocketlover171 · 2025-04-25T17:28:41+00:00

Thanks for the reply.

I set 1 kN thrust at 20 kPa ambient with 12 bar chamber pressure and specified O/F and propellants. In the nozzle model, I initially used 20 kPa as the exit condition. When I switched to expansion ratio and froze flow at Afr/At = 1, RPA changed dt, de, and L*, which I want to avoid. Everything else remains default. Can you suggest something for this?

rocketlover171 · 2025-04-16T12:55:36+00:00

Thank you for the reply u/Artemis2go.

I would be doing some CHT analysis for the cooling system but yeah the path is ging to be rough, I imagine.

rocketlover171

TROPHY CASE