Hi I am trying to simulate
 

Hi

I am trying to simulate a supersonic flow enteric a nozze of the shape
-----------------
--------------------
----------------------
--------------------------------------
INLET--------------------------------- OUTLET
----------------------
----------------------
-----------------

I am using rhoSonicFoam solver. My Inlet is supersonicInlet (U, P, T specified) with flow enetring at Mach 3. My outlet is exptrapolated outlet and I specified the walls to be adiabatic.

The solutions converges intitilally. A normal shock wave is formed that moves towards right until it reaches start of the converging section. After that the shock wave start moving towards left (towards inlet) and as it reaches the inlet the solution diverges.

Can somebody please help me wtih this.

Thanks in advace.

Varun

The shock wave will move to th
 

The shock wave will move to the smalles area of your nozzle in case the pressure inside the nozzle is really smaller than the outside pressure. Than the shock wave is "getting" the pressure to outside niveau.

Is it possible that this mechanism is vice-versa and the shock wave moves to bigger areas?
Maybe you should check on your pressure?

It's just a thought ...

Thanks Sebastian. I found o
 

Thanks Sebastian.

I found out a solution. Extending the domain far from the nozzle inlet/outlet, and applying the boundary conditions at these far boundaries solves the problem.

nozzle flow simulation
 

Dear Varun and all
if you have any example of nozzle flow simulation, share me please to tunzawcn@gmail.com.
Thanks

Looking for Qualified freelancer
 

Looking for qualified freelancer to simulate supersonic flow through C-D nozzle using fluent 6.2.16

please contact upal_arif@yahoo.com

Looking for qualified freelancer to simulate supersonic flow through C-D nozzle using fluent 6.2.16

please contact upal_arif@yahoo.com

Hello,
I'm looking for an example of a supersonic flow in a nozzle.
If you have that for me, you contact me at this email address: robdeb90@hotmail.com

Thank you.