Normalising of Lift Coefficient
 

Hello all,

As part of my dissertation I'm running some initial simulations with a supercritical aerofoil at low Mach and Re = 2*10e06. I am using the Spalart-Allmaras turbulence model as I want to be consistent with my later results. When comparing the Cp distribution with the wind tunnel they are quite similar but the problem is, the CL output by FLUENT seems to be normalised by the wrong reference value. (note. chord is different than 1 and reference length has been changed accordingly)

Is there anyone who has any ideas why this is happening?