Learning Forum

[XYZ098]

Hi, The nozzle that I am trying to model for a class project is for supersonic flow. I need suggestions to effectively model supersonic flow simulation using Fluent. What boundary conditions are used to define throat conditions? My current model is not showing flow transition after throat. And no shock waves exists at the exit of the nozzle. I think it is because i am not sure how to edit the boundary conditions to reflect supersonic flow for my model. Please provide a reference for the information you add to this post.

 

The geometry is attached 

[Rob]

Start here   https://www.youtube.com/watch?v=27zclV3c6oM

 

[XYZ098]

 I reviewed it. The nozzle I have is rectangular not circular. It does not have an axis of symmetry.  However, I am trying to build a model of the cross section to see if we get any results. My CAD model is for an experimental lab and it includes a section of the hardware in the lab before the CD nozzle.  We do not know the exact input conditions at the entrance of the nozzle but we calculated the input condition at the entrance of the geometry directly before the nozzle entrance. It is included in the two dimensional CAD model cross section shown in the attachments.

The sample results are attached and they are incorrect. The throat conditions are not matching the calculated values.         

[Rob]

The overall process is the same. For simulation you need to know the boundary & operating conditions: if you don't you'll need to extend the domain until you have the information, or find it out. 

As an aside, and often repeated, staff cannot download attachments so I have no idea what you posted. 

[XYZ098]

[Raef.Kobeissi]

Why don't you widen your exhaust domain? The geometry doesn't look like a CD nozzle??!