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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(sg6051-il) SG6051 | Selig / Giguere SG6051 wind turbine airfoil Max thickness 12% at 35.7% chord Max camber 3.1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sg6051-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6051-il | 50,000 | 9 | 35.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 50,000 | 5 | 34.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 100,000 | 9 | 58.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 100,000 | 5 | 57.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 200,000 | 9 | 82.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 200,000 | 5 | 78.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 500,000 | 9 | 113 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 500,000 | 5 | 102.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6051-il | 1,000,000 | 9 | 133.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6051-il | 1,000,000 | 5 | 115.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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