Dear Aurelien,
I don’t see anything odd between your airfoil polars at 10^6 and 10^7 Reynolds number. (However, the airfoil polars at 44.4% thickness and 48.1% thickness look a bit odd.) I don’t typically use AeroDyn’s Reynolds number interpolation, but I’m not aware of any problems with it either.
What Reynolds number is the interpolated AeroDyn result based on?
Best regards,