[Snacker]

Hello together,

I'm facing an issue with my airfoil validation where I'm getting significantly higher Cd (drag coefficient) values than expected. Interestingly, the Cl (lift coefficient) values are nearly spot on.

Here's what I'm using for my simulations:

• Airfoil length: 10 cm
• Airfoil widths tested: 10 cm, 1 m, 2 m
• Simulation box dimensions:
• 0.4 m in front of the airfoil
• 1.1 m behind the airfoil
• 1 m above and below the airfoil
• Boundary conditions: Symmetry planes to simulate an endless airfoil
• Solver: simpleFoam with kOmegaSST turbulence model
• Reynolds numbers: 2,000,000 and 1,000,000
• Wall treatment:
• High Reynolds number approach with an average y+ of 35
• Low Reynolds number approach with a y+ around 1

Despite these settings, my Cd values are almost double the expected values obtained from wind tunnel experiments.

If you need any more information or have suggestions on what might be causing this discrepancy, please let me know. Thanks in advance for your help!

Best regards,
Snacker

[Snacker]

Here is a link to the .tar files for Low and High Re calculations.

Files were to big for uploading it here.

https://drive.google.com/drive/folde...r8?usp=sharing