Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(du06-w-200-dt) DU 06-W-200 VAWT airfoil | DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT) Max thickness 19.8% at 31.1% chord Max camber 0.5% at 84.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (du06-w-200-dt)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du06-w-200-dt | 50,000 | 9 | 11 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 50,000 | 5 | 16 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 100,000 | 9 | 32.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 100,000 | 5 | 36.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 200,000 | 9 | 48.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 200,000 | 5 | 51.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 500,000 | 9 | 71.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 500,000 | 5 | 71.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du06-w-200-dt | 1,000,000 | 9 | 90.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du06-w-200-dt | 1,000,000 | 5 | 87.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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