
[Sponsors] 
Supersonic Inlet for a Compressible Flow in a Nozzle 

LinkBack  Thread Tools  Search this Thread  Display Modes 
October 10, 2012, 11:56 
Supersonic Inlet for a Compressible Flow in a Nozzle

#1 
New Member
Join Date: Aug 2012
Posts: 9
Rep Power: 12 
Hi!
I am trying to solve a compressible flow in a diverging converging problem. I am using the mesh given in the cornell problem: https://confluence.cornell.edu/display/SIMULATION/Fluent++Compressible+Flow+in+a+Nozzle The difference from the cornell tutorial is that I want to solve it for a Supersonic flow at the inlet. as if it was a diffuser. the area ratio A_inlet/A_t=3.5 I use Pressure Inlet with: P_total=101325, P_static=3733.8, T_total=765.2 which are the A/A* values for a the 1D isentropic problem. for the outlet I use Pressure Outlet with:P_static=3733.8, T_total=765.2 I am trying to reach supersonic inlet to sonic throat to supersonic outlet. I am solving it in steady state. the problem is that the program completely diverges after a few iterations and keeps on diverging. I tried refining the mesh with "Adapt" tool but it doesn't seem to help. What am I doing wrong? I have searched all over and I don't seem to find info about how to solve a problem with a Supersonic Inlet. maybe the problem is in the steady state? thanks! 

October 10, 2012, 15:14 

#2 
Member
NormalVector
Join Date: Oct 2010
Posts: 71
Rep Power: 14 
Which solver diverges first? That may be a hint. I've had divergence problems before and if I underrelax the solver that diverges first a little bit (~0.05 to ~0.1 change) it helps.


October 10, 2012, 15:28 

#3 
New Member
Join Date: Aug 2012
Posts: 9
Rep Power: 12 
Thanks for the tip. I'll be sure to try it.
I'll post what happens when I get to it. 

October 10, 2012, 16:08 

#4 
Member
NormalVector
Join Date: Oct 2010
Posts: 71
Rep Power: 14 
Sure. It may take more a more aggressive relaxation effort than a 0.1 change so you can try that as well.


October 12, 2012, 11:19 

#5 
New Member
Join Date: Dec 2011
Posts: 6
Rep Power: 13 
hi,
i want to put sinusoidal pressure inlet, is it possible in fluent? 

October 14, 2012, 04:16 

#6 
New Member
Join Date: Aug 2012
Posts: 9
Rep Power: 12 
to your question wissou22, yes you can do it in fluent.
One way I know of is by UDF (User Defined function). check out Tutorial 4:Modeling Transient Compressible Flow in the FLUENT 12.0 tutorial guide. they do exactly what you want, only they do it at the outlet. NormalVector, I am solving the problem in a densitybased solver and I don't see an option for inputing relaxation parameters anywhere.. also at that subjet, If I'm solving a problem that should be supersonic (or sonic) in all the domain, What is the best solver to use? I used the density solver with its default settings: Formulation: Implicit Flux Type: RoeFDS Gradient: Least Squares Cell Based Flow: Second Order Upwind Are those settings good for supersonic flows? Thanks 

November 7, 2012, 21:43 

#7  
New Member
Yao, Cheng
Join Date: Nov 2011
Location: Harbin
Posts: 7
Rep Power: 13 
Hi, Daco.
I'm doing a similar work as you did. :) My simulation begins with 1st order Upwind scheme. It works well. But when I use 2nd order Upwind scheme, it diverged. Some people tell me, there isn't flux limiter in FLUENT. So it must diverge because of the numerical oscillation when using the 2nd upwind scheme. However, I don't how to get a 2nd order result in FLUENT. And they suggest CFX to me, since it has resolution scheme. Maybe the problem can be solved in CFX. The geometry I used in my work is similar to Anderson's. And his report is available as follows. http://ntrs.nasa.gov/archive/nasa/ca...1970018205.pdf http://ntrs.nasa.gov/archive/nasa/ca...1971017509.pdf If you get some improvement, please let me known: slaonslaon@gmail.com . Thanks. :) Quote:


November 7, 2012, 23:51 

#8 
New Member
Join Date: Aug 2012
Posts: 9
Rep Power: 12 
Well, I have a partial answer because I left this project.
I found out that for the implicit solution method the program is completely divergent. When I tried Explicit it actually worked without exploding but it also didn't converge and the error monitor always moved around 10^1. So I suggest using the explicit method for supersonic inlets. Next, I think I had some problems with my geometry so I think some of my problems were caused by that. I reached a conclusion that because the geometry begins at the inlet without any straight geometry with a uniform flow before it, when a shock wave started to form at the inlet opening the program couldn't converge. so here I suggest when dealing with a condivnozzle use an initial straight geometry before the walls start to converge. Maybe even create a mesh outside the nozzle to see if a shock wave forms on the lips of the opening. Like I said I left this project and didn't reach a good converged solution. All I said here is only my conclusions while working so don't take it as a 100% truth. Isn't it silly that its very hard to solve a very simple case in a large commercial CFD program like FLUENT? I really don't get it.. Thanks! 

November 8, 2012, 03:34 

#9 
New Member
Yao, Cheng
Join Date: Nov 2011
Location: Harbin
Posts: 7
Rep Power: 13 
Thank you for your reply and suggestion.
:) 

Thread Tools  Search this Thread 
Display Modes  


Similar Threads  
Thread  Thread Starter  Forum  Replies  Last Post 
Difficulty running an inviscid compressible nozzle flow using OpenFOAM  rbozinoski  OpenFOAM Running, Solving & CFD  11  December 29, 2015 07:19 
compressible flow calculation error using rhoSimpleFoam solver  student4326  OpenFOAM Running, Solving & CFD  7  November 2, 2015 11:34 
Modeling Laval nozzle, subsonic flow to supersonic  Bloshchitsyn Vladimir  CFX  2  June 18, 2007 05:18 
compressible two phase flow in CFX4.4  youngan  CFX  0  July 1, 2003 23:32 
what the result is negatif pressure at inlet  chong chee nan  FLUENT  0  December 29, 2001 05:13 