Force coeffients at 87% blade span
 

Hi all,
I'm simulating a rotating helicopter rotor with varying pitch in Star-CCM+. I want to measure the lift CL and drag Cd coefficients or even better the normal coefficient Cn at 87% along the blade span. I want to plot these values as they vary with azimuth.
Can anyone help?:confused:

if you explain this with less aero terms then others might understand eg draw an image since i imagine it will be possible using thresholds and reports