[Wingman]

Hi,

I have experimental data for an airfoil.
Lift coefficient as function of aoa Cl(α) and drag coefficient as function of aoa Cd(α).

I have also modeled this airfoil with several turbulent models which I want to compare to the results of the experiment to see which one has the best "score".

I've read some papers and some use percentages (f.ex. "results were within 5%...") but I don't really like that method... Because, for example, if the numerical error would be a constant of 0.01 from the experimental... the error of of Cl = [0.01 ; 0.1 ; 0.25 ; 0.5 ; 0.75 ; 1 ; 1.25 ; 1.5] at angle of attacks [0 1 2 3 4 5 6 7 8], would become [100% ; 10% ; 4.0% ; 2.0% ; 1.3% ; 1.0% ; 0.8% ; 0.7%] respectively. - And I don't think that would be a fair for comparison.