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,

Thanks so much for your reply and dedicated help.

I totally agree with you that the lift force is to be zero at 0 angle of attack.

Actually, I am not sure what it is the float values refer to, but yeah, at different octree settings, I get different values for lift. Even more, I get lift coefficient sometimes at order of magnitude 1e-4 and 1e-3 and that of drag is 1e-2.

Is this normal to happen? Is this numerically acceptable?

Do I need to input the thickness of first layer that capture the boundary layers to get more accurate result?
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0 hossam over 3 years ago

Hello Chuel,

Thanks so much for your reply and dedicated help.

I totally agree with you that the lift force is to be zero at 0 angle of attack.

Actually, I am not sure what it is the float values refer to, but yeah, at different octree settings, I get different values for lift. Even more, I get lift coefficient sometimes at order of magnitude 1e-4 and 1e-3 and that of drag is 1e-2.

Is this normal to happen? Is this numerically acceptable?

Do I need to input the thickness of first layer that capture the boundary layers to get more accurate result?
Cancel
Vote Up 0 Vote Down

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Verify Answer

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