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July 9, 2018, 03:07
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Issues with the drag coefficient
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#1 |
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New Member
Ramesh
Join Date: Jun 2018
Posts: 8
Rep Power: 9  |
I am simulating flow past a NACA 0012 airfoil.
I find that the Cl values are proper but the Cd values are a bit high compared to the values that must be obtained. Am I missing any condition that must be applied? Thanks in advance, Rookier |
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July 9, 2018, 20:49
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#2 |
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Senior Member
Join Date: Mar 2015
Posts: 892
Rep Power: 19 |
What is the Reynolds number, have you done a mesh convergence analysis and what are the expected and calculated values of the lift and drag coefficients? Ensure that the reference values are correct if you are using the inbuilt lift and drag reports.
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July 10, 2018, 02:35
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#3 |
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New Member
Ramesh
Join Date: Jun 2018
Posts: 8
Rep Power: 9 |
Thank you for replying...
The Reynolds number is 3*10^6. I have given the inlet reference values. The lift coefficients come out to be good enough.Am only facing problem with the drag co-efficients |
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July 10, 2018, 05:31
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#4 |
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Senior Member
Join Date: Mar 2015
Posts: 892
Rep Power: 19 |
What turbulence model are you using and what are the y+ values? This discussion appears to be relevant: Fluent airfoil help
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