[araina85]

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.

[HyperNova]

Did you define the project area correctly ?

[araina85]

yes. I have a 1m chord with a 1m depth.