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Incorrect Cl and Cd data for a 3D airfoil

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Old   November 13, 2014, 11:13
Default Incorrect Cl and Cd data for a 3D airfoil
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raina
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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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Old   November 13, 2014, 13:31
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B_Kia
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Did you define the project area correctly ?
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Old   November 13, 2014, 15:09
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raina
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yes. I have a 1m chord with a 1m depth.
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3d airfoil, drag coefficient, lift coefficient

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