[mechie.2003]

Hello everyone, I hope you all are doing well and wish you all good health.

So I did a steady state, pressure based simulation of NACA 2412 airfoil on 0 degree angle of attack and on maximum lift (at 15 degrees for 2412) using Spalart-Almaras model with Strain/Vortex corrections (Energy eqn Off).

For my better understanding I first watched a Youtube video on NACA 4412 simulation by Anthony T (https://www.youtube.com/watch?v=nzvEvLCxOss&t=2228s). After watching the video, I attempted the 4412 simulation by myself before doing the 2412 simulation.

I created a C-type mesh for my 2412 airfoil (the same way as showed in the video) and got about 200k nodes and elements with 0.28175 min orthogonal quality and 0.59857 max skewness.

After running the 2412 simulation for 1000 iterations I compared experimental values against my simulation values and found 5-13% error in Lift coefficients and 1-42% error in Drag coefficients respectively for both cases at both conditions (0 degrees and max lift). I found the same percentage of error in NACA 4412. Even after doing some refinements I obtained results with the same kind of error range.

Is the error reasonable? If not, is there anything else that needs to be done to minimize the error range?

P.S Screenshots attached below for reference.

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