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September 7, 2019, 17:06 |
CFD analysis for leading edge airfoil
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#1 |
New Member
Join Date: Jul 2019
Posts: 5
Rep Power: 6 |
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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September 8, 2019, 02:26 |
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#2 | |
Super Moderator
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Quote:
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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September 9, 2019, 07:59 |
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#3 |
New Member
Join Date: Jul 2019
Posts: 5
Rep Power: 6 |
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. |
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