[nicola_salin]

Hi everyone,
I've written a panel code that solves a potential flow around wings. After that in the same code I've added a viscous correction (boundary layer equations for laminar and turbulent layers). The issue that I'm struggling with is: how should the aerodynamic coefficients change from a potential solution to a potential solution that considers the viscosity of the air? Both cases consider same geometry, same angle of attack (small AOA), same flow speed. In short, is that correct that CD and CL are a bit lower with a viscous solution rather than with a inviscid solution?
Best regards,
Nicola Salin