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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(s6062-il) S6062 8% | Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s6062-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s6062-il | 50,000 | 9 | 34.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 50,000 | 5 | 35.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 9 | 50.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 9 | 65.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 200,000 | 5 | 58.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 9 | 82 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 500,000 | 5 | 68.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 9 | 91 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6062-il | 1,000,000 | 5 | 73.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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