hi everybody i'm new of Ope
 

hi everybody

i'm new of OpenFOAM and i'm working on the characterization of a NACA 0015 with several turbulence models. Anyway, i really would like to plot the pressure coefficients along the profile. I did a C grid with gmsh with two surfaces (upper & lower) on the profile. The solvers seems right (now i use the Spalart-Allmaras with simpleFoam).

How can i get the values of the pressure at the surface points and the position of those points?

thanks a lot

it works great thanks a lot
 

it works great

thanks a lot

cheers

hi everybody i am w
 

hi everybody


i am working on naca 4421 airfoil case...i am facing difficult to give different angles of attack for this airfiol..can u please help me how and where to give AOA in openfoam 1.4.1..

Dear Naveen, Hope you are b
 

Dear Naveen,

Hope you are beginner to openFOAM. So before trying new cases, why not you try some tutorials in openFOAM. It will build up your basic understandings about openFOAM. All your doubts will clear if you understand the tutorials.

For specifying AOA you have to edit the file "U" under the directory "0". Here you should enter the values of x y z co-ordinates.

thanks velan sir for replying.
 

thanks velan sir for replying....

i did naca 0012 airfoil case in gambit and now i need to import it into openfoam 1.4.1...can u please tell me how to import it into openfoam...and also i need naca 0012 vertices to create geometry in openfoam 1.4.1....

How did you created the mesh i
 

How did you created the mesh in gambit without its vertices ?
If you have mesh in gambit, then export the mesh in .msh format.

Then copy the mesh into case directory and do
fluentMeshToFoam

There is one nacaAirfoil example in Tutorial(OpenFOAM/OpenFOAM-1.5/tutorials/sonicTurbFoam/nacaAirfoil). Try to understand.

Onemore thing, many people told that post a forum in new thread. Dont spam it. Try to use Start New Thread.

Did you get an answer??
I need the same!

Thanks for replying!

Hey,

Use paraview and make sure your flow has become steady. Then, in object inspector, choose only the boundary name given to describe the surface of the airfoil and apply. Use the slice filter and slice along the symmetry plane of your mesh. On 're-sizing to fit' you should see only the closed loop around the surface of the airfoil. Choose the variable 'p'. Use the calculator filter to get Cp value and rescale to fit data range. You should be able to see the Cp variation. You can also plot it externally by saving the data to an external file.

Hope this helps!

Thank you very much!