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February 12, 2018, 07:32 |
Naca 4412 @aoa 2
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#1 |
New Member
Vishish Behera
Join Date: Jan 2017
Posts: 7
Rep Power: 9 |
I am simulating a simple NACA 4412 airfoil with velocity = 2m/sec @AOA 2. This Cl value is coming quite low, around 0.38 where it should have been 0.69.
I have tried using both Spallart and K-omega turbulence model, and there is nothing wrong with the mesh and the geometry. Can anyone figure out what the problem might be. It's really bugging me now. |
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February 12, 2018, 08:35 |
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#2 |
Member
Join Date: Apr 2016
Posts: 53
Rep Power: 10 |
Hi
I don't have much experience with Fluent. But I suggest you to check the reference values once. Following links may be helpful. https://www.sharcnet.ca/Software/Flu...g/node1207.htm Reference Values- Reference Area Reference values in FLUENT Best of luck |
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February 12, 2018, 09:12 |
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#3 |
New Member
Vishish Behera
Join Date: Jan 2017
Posts: 7
Rep Power: 9 |
I did try changing the reference area. But no luck there too. The value comes absurd.
Is it due to the low velocity? |
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