Hello guys, I am trying to study the flow around NACA0012 airfoil at zero angle of attack. However, when I try to refine the octree parameter around the airfoil and generate the mesh, every single time I get different values for Lift force! Any reasons??

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0 hossam over 3 years ago

Hello Chuel,

Apologies for my late reply.

Ok, now I get it. Thanks for enlightening me regarding this issue.

I have one last question about this topic. When I enter an angle of attack, as velocity components in x and y direction, I don't get correct values for lift and drag.

For example, I tried to replicate the same value in your excel screenshot with same octree size(=1mm). At AOA(=zero degree), I obtained a similar value as yours for lift coefficient and at the same order of magnitude, however, at AOA(=2degrees), I obtained value of ~0.052! That's not correct, I think I misunderstand something in the setup, so could you please help me?

Hint: I used static pressure outflow as an outlet BC. for your consideration.
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0 hossam over 3 years ago

Hello Chuel,

Apologies for my late reply.

Ok, now I get it. Thanks for enlightening me regarding this issue.

I have one last question about this topic. When I enter an angle of attack, as velocity components in x and y direction, I don't get correct values for lift and drag.

For example, I tried to replicate the same value in your excel screenshot with same octree size(=1mm). At AOA(=zero degree), I obtained a similar value as yours for lift coefficient and at the same order of magnitude, however, at AOA(=2degrees), I obtained value of ~0.052! That's not correct, I think I misunderstand something in the setup, so could you please help me?

Hint: I used static pressure outflow as an outlet BC. for your consideration.
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