Hi Everyone, I'm fairly new
 

Hi Everyone,

I'm fairly new to OpenFOAM and I am having troubles in setting the boundary conditions for a simple test case in potentialFoam. I'm trying to simulate external flow over a NACA airfoil at 14 degrees AOA.

I don't have any problems in obtaining a solution with potentialFoam, icoFoam or simpleFoam when the angle of attack is low (0 to 5 degrees). However, for large AOA, there is an outflow on my INLET patch and it seems to cause problems.

My mesh is a C-mesh (it can be viewed at NACA0012 mesh ). The INLET patch is the patch on the left (C-shaped) and the OUTLET patch is the patch on the right. My boundary conditions are as follows:

U:
INLET type inletOutlet;
value (40 10 0);
OUTLET zeroGradient;

p:
INLET type outletInlet;
outletValue 0;
OUTLET fixedValue;
value 0;

The velocity field I obtained can be seen here: velocity field 1. I also tried the following:

U:
INLET: fixedValue (40 10 0)
OUTLET: zeroGradient
p:
INLET zeroGradient
OUTLET fixedValue 0;

But then I get the following: velocity field 2. Like I said, I don't have much experience with boundary conditions in OpenFOAM so I was wondering if anyone could help me.

Thank you for your time

Patrice

Hi Patrice Castonguay
 

Hi Patrice Castonguay


This venkatesh from india i am working on NACA0012 Airfoil which is imported from fluent.
Now i need to solve it for Euelrs equqtions with incompresible flow can u tell me procedure for that
with mach number .85

hi venkatesh, instead of usin
 

hi venkatesh,
instead of using fluent file u can use .msh file from gambit and change to foam format by using fluentMeshToFoam command which will change the gambit mesh file to foam mesh file.
then u can copy simple foam folder in ur login name folder there u will get boundary file inside ur control folder.
copy that details in ur 0 file and edit ur boundary condition .it ask there for how much mach no ...
try this out iof any prob mess me back

HI Patrice Castonguay Sir
 

HI Patrice Castonguay Sir

This is Venkatesh from india working on NACA0012 AIRFOIL can u please send me the procedure u solved for the 0 - 5 AOA.........