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Angle of attack input for simpleFoam analyses

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Old   March 25, 2012, 21:48
Default Angle of attack input for simpleFoam analyses
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Hello,

As a new user, I have a question on angle of attack input for airfoil analyses using simpleFoam. Is the angle of attack inputted during the process when the blockMeshDict is created (i.e. meshing process), or in the "U" velocity file when the freestreamValue is set for the velocity conditions for each of the boundaries. I would appreciate any guidance on this.
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Old   March 26, 2012, 02:55
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It doesn't make any difference. You can either set your domain at the angle of attack you want and then have the flow entering the inlet plane and going along one direction (say x) or you can have your domain at 0░ and then set your flow to enter the domain at the angle you want, in this case you'll probably have to set 2 faces of the domain as an inlet. Of course, if you want to simulate many angles of attack the latter solution is the best because changing the angle of attack would be easier and, more important, your mesh wouldn't change as you change it.
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Old   March 26, 2012, 10:04
Default angle of attack question answered
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lovecraft22,

Thank-you for your help in clarifying the ways to set the angle of attack.

Regards,
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Old   December 23, 2013, 22:57
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Quote:
Originally Posted by lovecraft22 View Post
It doesn't make any difference. You can either set your domain at the angle of attack you want and then have the flow entering the inlet plane and going along one direction (say x) or you can have your domain at 0░ and then set your flow to enter the domain at the angle you want, in this case you'll probably have to set 2 faces of the domain as an inlet. Of course, if you want to simulate many angles of attack the latter solution is the best because changing the angle of attack would be easier and, more important, your mesh wouldn't change as you change it.

I understand the thread is quite old, but is there a way to set the b.c. with an angle of attack in OpenFOAM? Much would be appreciated for any answers on this?

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Old   December 24, 2013, 11:40
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Well, if you set your inlet as a velocity inlet, then you can set any angle of attack you want simply by imposing two components of the velocity vectorů

So, if your flow is mainly in the x direction and the lift direction of your airfoil is in the z direction and you want to impose V as velocity with an angle of attack A, then you just need to set (V*cos(A),0,V*sin(A)) as your inlet velocity.
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Old   December 25, 2013, 03:05
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Originally Posted by lovecraft22 View Post
Well, if you set your inlet as a velocity inlet, then you can set any angle of attack you want simply by imposing two components of the velocity vectorů

So, if your flow is mainly in the x direction and the lift direction of your airfoil is in the z direction and you want to impose V as velocity with an angle of attack A, then you just need to set (V*cos(A),0,V*sin(A)) as your inlet velocity.
Hi Lore,

Thanks for your quick reply.

Say the computational domain is a rectangular. If the inlet flow is in x direction, then side b.c. (two boundaries parallel to the inlet flow) could be set as symmteryPlane, and outlet velocity could be set as zeroGradient. But these b.c.s are no longer validated if the attack angle is non-zero. Then how to change the sides and outlet boundary conditions accordingly?
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Old   December 25, 2013, 12:13
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You'll need two inlets + two outlets and you can keep the side walls as symmetry.
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Old   December 29, 2013, 22:15
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Originally Posted by lovecraft22 View Post
You'll need two inlets + two outlets and you can keep the side walls as symmetry.
Hi Lore,

Could you please elaborate on "two inlets + two outlets"? As there are only four boundaries, how do you set these boundaries + side symmetry?
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Old   December 30, 2013, 03:21
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Well, if your domain is rectangular then you have 6 walls which mean 6 boundary conditions to apply.

Now, let's consider a positive value of the angle of attack ( meaning your airfoil is probably generating lift) so that the flow is coming from under the airfoil. To this extent, the bottom wall and the front wall (the one facing the leading edge) will have to be set as inlets as the flow is entering your domain from there. The upper and back wall (the one facing the trailing edge) will have to be set as outlets as the flow is going out of there. The lateral walls instead can be set as symmetry/empty/or whatever you need them to be for you case.
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Old   January 5, 2014, 22:59
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Quote:
Originally Posted by lovecraft22 View Post
Well, if your domain is rectangular then you have 6 walls which mean 6 boundary conditions to apply.

Now, let's consider a positive value of the angle of attack ( meaning your airfoil is probably generating lift) so that the flow is coming from under the airfoil. To this extent, the bottom wall and the front wall (the one facing the leading edge) will have to be set as inlets as the flow is entering your domain from there. The upper and back wall (the one facing the trailing edge) will have to be set as outlets as the flow is going out of there. The lateral walls instead can be set as symmetry/empty/or whatever you need them to be for you case.
Hi Lore,

Many thanks for your answers and patience. Now, it works pretty well with freesteam b.c. condition by two inlets and two outlets. Great help.
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