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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(sg6040-il) SG6040 | Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sg6040-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6040-il | 50,000 | 9 | 26.1 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 50,000 | 5 | 26.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 9 | 50.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 9 | 72.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 5 | 68.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 9 | 96.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 5 | 88.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 9 | 114.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 5 | 102.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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