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CFD analysis for leading edge airfoil

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Old   September 7, 2019, 17:06
Default CFD analysis for leading edge airfoil
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Hi, I am currently doing simulation on NACA 4412 airfoil but the lift obtained is ridiculously large (like 10^81). I have constructed lines for the structured mesh but the result is still the same.
f1.JPG

f2.JPG


My project is based on the following paper.

A parametric study on leading-edge slots used on wind turbine airfoils at
various angles of attack

Please give any advise or suggestion. Thanks in advance.
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Old   September 8, 2019, 02:26
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Quote:
Originally Posted by JYLEE View Post
Hi, I am currently doing simulation on NACA 4412 airfoil but the lift obtained is ridiculously large (like 10^81). I have constructed lines for the structured mesh but the result is still the same.
Attachment 72112

Attachment 72113


My project is based on the following paper.

A parametric study on leading-edge slots used on wind turbine airfoils at
various angles of attack

Please give any advise or suggestion. Thanks in advance.
There are couple of issues. As this problem is very simple:

1. Units are not properly set. Or mesh is not scaled properly.

2. Reference values are not set correctly.

3. Mesh is not good enough

You can try ICEMCFD, it will give you much better control. You can also go for hybrid mesh. Mesh slot region with tetra elements.
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Old   September 9, 2019, 07:59
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Sir, thanks for the reply. I constructed the geometry with spaceclaim and i realize that I have too many Boundary Conditions.
BC.JPG

What value should I put for the turbulence intensity and the length scale ? I am getting back flow at the outlet according to the console.

Here is my convergence plot for the parameters and the lift

[ATTACH]div-lift.JPG[/ATTACH]

Thanks in advance.
Attached Images
File Type: jpg div-residual.JPG (59.8 KB, 5 views)
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