[spraveeng]

i have checked the grid and it doesn't have any problem i guess...
is there any method to find the errors in grid???

Solution for NACA 0006 is converging for 3 different angle of attacks @ 0,2,4 degrees after that if i increase further the angle of attack it is not converging

earlier my residual values are 1e-06

and please explain about k-epsilon model (give me some reference links to follow)

please do reply its important for me

[Edward!]

i have checked the grid and it doesn't have any problem i guess...
is there any method to find the errors in grid???

Solution for NACA 0006 is converging for 3 different angle of attacks @ 0,2,4 degrees after that if i increase further the angle of attack it is not converging

earlier my residual values are 1e-06

and please explain about k-epsilon model (give me some reference links to follow)

please do reply its important for me[/QUOTE]

Ok!
You have to check the mesh in fluent "CHECK GRID" that is the first step if you want to simulate correct!! and fluent will tell you if your case is correct or not!!!

Later on! check the tutorial number one for gambit!, you will find how can check the quality of the mesh; you work with 2D meshes so you coudnt have deformation volumes if your work with 3D your deformation volumens should be <0.8

After that, check the boundary layer specially in the trailing edge, in all the profile; becouse some nodes have problems with the surface of the profile!!
Make a Zoom in the profile surface!!!

That comfirms if incrase the angle of atacks you will have reversible flow!!


Book An introduction to computational flud dynamics
The finite volume method H.K. Versteeg and W. Malalasekera

The book is easy to understand


I work with Turbomachinery; with turbine blades!! is diferent and more complicated but also is similar

I hope this work!!!

Greetings

[tgrt18]

Originally Posted by Etesh

Hi Simon,

With the help of your videos I am now able to make Hexa mesh of 2D Wind Turbine but now I am having trouble assigning the boundary condition in Fluent. I guess the problem is when I convert Structured Hexa mesh to Unstructured mesh, it automatically creates LINES under the Mesh tab in display tree and then Fluent considers those lines as a Boundary condition. so my question is how can I get rid of those lines and have the same BC as I assigned them in ICEM?

Attached is the Tin and Blk files.

Thank you.

in a CFD point of view you should preserve the wake intensity behind your model by refining the mesh in the tail. it will affect your solution later

[antonio joao]

hello
i tried to open a mesh that i did in ICEM in fluent but the error message "unbound variable" appeared, could anyone help me?

thanks

[diamondx]

i googled that error, some people faced that problem because they named their boundaries with spaces like "inlet 1" instead of "inlet_1".
Icem won't let you name it that way, check you boundaries, how they are exported, you will find more post if you google that error

[antonio joao]

thanks, I don´t thinks this is what´s is wrong in my case.
ill give it a try in google also. just to inform, this is actually a tutorial that I did but not being able to open the mesh in fluent...here is the link just in case anyone wants to see it

http://www.youtube.com/watch?v=6wQPeBpvwCk