[robbie578]

Hello..
I wanted to analyse the flow around the NREL S822 and S823 airfoil for wind turbine blade design purposes. It's a 2D analysis and i used the C mesh style. I tried analysis through various models, ranging from inviscid to Reynolds SST, basically the whole thing. I'm a bit new to ansys, so i didn't change any values in any of those models. Anyway, the issue is, the Cl and Cd values that i get from the analysis, are almost 90% less than the experimental values (using the k-epsilon model with enhanced wall function). The crazy thing is that, the difference of 90-95% seems stable across a large number of Angle of Attack.
The next issue is that, even after the flow seperates as the AOA increases, the lift seems to keep on increasing.
Only if i can get the Fluent results approximately equal to my experiential results, can i proceed further in my project.
Please help me out here. What should i do to correct all these ??