Plotting and calculating Coefficient of lift/drag/moment for an airfoil in Paraview
 

I am trying to get plots for coefficients of lift, drag and moment vs time/ angle of attack for an oscillating NACA0012 airfoil. I have calcuated the lift and drag using Extract Surface > Generate Surface Normals> Calculator (p*normals_Y for lift, p*normals_Z for drag)> Integrate Variables.

I would now like to plot Lift and Drag against time/ angle of attack but I can not find a way to do this. I cannot select lift or drag as one of my variables in the Data Analysis tab for 'plot selection over time' or 'plot global variables over time'. I would further like to calculate the Coefficients of Lift/ Drag and Moment and plot these over time/angle of attack.

Any advice on how to plot these on ParaView and how to calculate their coefficients would be greatly appreciated.