When running an analysis of an airfoil, i am getting Cp values greater than 1, even after referencing the inlet velocity and setting the operating pressure to zero. Does anyone have any advice on how to solve this?

Thankyou all

same old question and same old answer, refine the meshes near to the walls of airfoil. Cp values depend on the pressure gradients very much so if you can resolve pressure gradient nicely near the walls , you can get good values of Cp