Learning Forum

[Inaam Hussain]

Dear Ansys Users, 

I am trying to simulate transonic flow around a circle and square( at 0 and 45 degrees angle of attack); it seems to be converging fine at the CFD scaled residuals and it's working fine at mach 0.4. But when you go faster at mach 0.6 and beyond, the screen shows this:

 

 

 

 

 

 

 

 

I don't see what's wrong with the flow CFD residuals console, but I saw that the highest mach number visualization is about a thousand, so how do I correct this predicament? And control Ansys fluent so it gives the right computed values and correct visualization?

All the best,

Inaam Hussain

 

[Inaam Hussain]

 

 

Here is the visualization of the interrupted flow's mach number at 0.6, and the CFD residuals for the square as well as the meshing, along with the circle meshing as well :

 

 

 

 

 

So I was wondering whether any of the ansys employees can help me simulate transonic flow around a circle and square ( in straight up  0 degrees angle of attack and double wedge form at 45 degrees angle attack.

 

All the best,

Inaam Hussain

[Rob]

It's likely a problem with the mesh - ortho quality under 0.1 ish is poor, below 0.01 is awful. Depending on where those cells are you may find as the speed increases the solver numerics can no longer counter the mesh. 

Looking at the decompostion in the images check how you've set the sizing around the object of interest. You also need to read up on blockage factor for experimental work: the object is large compared to the duct. If you want to model the object in "open" space you may have a problem.