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
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