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November 13, 2014, 11:13 |
Incorrect Cl and Cd data for a 3D airfoil
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#1 |
New Member
raina
Join Date: Oct 2014
Posts: 2
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I am trying to model a 3D airfoil i.e. an infinite airfoil section to obtain and compare the lift and drag coefficients to that obtained from 2D. In principle, the 2D and 3D data should match. I am under-predicting the lift by ~50% and over-predicting drag by ~60%. I was using a k-w SST model for my simulations.
Given the incorrect results, I went back and simulated the 3D airfoil assuming no viscosity (inviscid solution). But even this solution provides me with a cl that is lower than the viscous experimental data. Any ideas as to what I am doing wrong? I could attach my case files if required. |
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November 13, 2014, 13:31 |
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#2 |
Senior Member
B_Kia
Join Date: May 2014
Location: Ir
Posts: 123
Rep Power: 12 |
Did you define the project area correctly ?
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November 13, 2014, 15:09 |
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#3 |
New Member
raina
Join Date: Oct 2014
Posts: 2
Rep Power: 0 |
yes. I have a 1m chord with a 1m depth.
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Tags |
3d airfoil, drag coefficient, lift coefficient |
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