[andrei.cimpoeru]

Hi Foamers

I am simulating the flow over NACA23012 and it seems that when i change the angle of attack i am getting the same results. for example i changed from 0 deg to 5 deg using the Velocity*cos(angle) in x direction and Velocity*sin(angle) for y direction but the results seems to be the same even after i defined the angle of attack ..weird............. Might my inlet faces....what do you think?

Any suggestions......?

Thanks

[flotus1]

What does your computational domain look like? What other boundary conditions do you have besides the velocity inlet?
A sketch or even a screenshot might be helpful.

And which soler are you using?

[andrei.cimpoeru]

Originally Posted by flotus1

What does your computational domain look like? What other boundary conditions do you have besides the velocity inlet?
A sketch or even a screenshot might be helpful.

And which soler are you using?

Thanks for reply

below i attached my sketch and sorry for the poor quality but you can understand ... I am using k omega sst and simpleFoam. solver
the wall represents my domain ... The inlet is defined 10 meters away from the wall and the outlet is defined 15 m away from the trailing edge.......

Thanks again

[Aeronautics El. K.]

And the chord length is? I mean, if the chord is 1m in length I believe the boundaries are too close. They should be at approximately 20c away.
Something else, I don't know how openfoam works, but you should check whether it uses angles in degrees or in rads.

[flotus1]

Just like I thought...

The straight boundaries (symmetry I guess) at the top and bottom of your domain guide the flow towards an AoA of 0°. No matter what you specify at the inlet.

[Far]

Yes for AOA study you should modify domain to circular at inlet and boundaries should be placed at 15-20 C at inlet and 25-30 C at outlet.