Sectional lift coefficients
 

How would you calculate the lift coefficient on a section? In this case, I am simulating a 3D wing and would like to plot the lift distribution along the span. Any help would be appreciated.

You can have a look at accumulated force tables. They can be used to plot lift and drag forces on surfaces. There's also a normalization option so you can plot the coefficients. I have never used this feature though, I don't know if that might help you. There is a how to video in the support center if you have access (KB33001).