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CFD Simulation of a Rocket Engine Nozzle: Divergence Issue (Want to see nozzle plume)

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Old   May 12, 2017, 15:25
Default CFD Simulation of a Rocket Engine Nozzle: Divergence Issue (Want to see nozzle plume)
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Vinayak Deshpande
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Dear All,

I am trying to perform a turbulent (k-epsilon) compressible flow simulation through a rocket engine nozzle with the following conditions:
Inlet P: 2 MPa, T: 900 K
Outlet: Vacuum

Here is my mesh and boundary region:
Inlet is : nozzle entry, and outlet is: the domain beyond the nozzle exit.

An image can be found here:
https://gyazo.com/bb7e493437eab39a5ae9f861f728be34

The turbulence model I use is k-epsilon, and the Operating condition is set to 0
Gauge Pressure at Inlet: 2 MPa, and outlet: 0 Pa

I am not sure why this solution seems to diverge, I think I am defining the boundary condition wrong. What must I do to fix this?

The mesh is pretty dense (4mm max size) - The nozzle outlet is 82 mm

I would appreciate if someone could shed some light on this error and help me fix this issue.

Kind Regards,

Last edited by VinayakDesh; May 15, 2017 at 12:18.
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Old   May 12, 2017, 16:46
Default Dear admin, please close this thread
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Vinayak Deshpande
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I have figured it out, thank you
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Old   February 28, 2018, 22:07
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Song Guoqing
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Quote:
Originally Posted by VinayakDesh View Post
I have figured it out, thank you
hi
I have recently solve the resemble problem as you.
here is my case set
turbulence model: S-A
inletressure inlet 3Mpa,1000K
outletressure outlet 1.01KPa,300K
wall:idiabat wall
mesh is fine.
I am not sure why this solution seems to diverge,either
can you tell me how to do with it,thank you

Kind Regards
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Old   February 1, 2022, 06:24
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Alessandro
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Hi can you please explain to us how did you solve the problem?
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Old   February 2, 2022, 21:57
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