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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(s2060-il) S2060 8% | Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s2060-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2060-il | 50,000 | 9 | 36.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2060-il | 50,000 | 5 | 36.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2060-il | 100,000 | 9 | 53.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2060-il | 100,000 | 5 | 50.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2060-il | 200,000 | 9 | 70.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2060-il | 200,000 | 5 | 62.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2060-il | 500,000 | 9 | 91 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2060-il | 500,000 | 5 | 75.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2060-il | 1,000,000 | 9 | 101.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2060-il | 1,000,000 | 5 | 79 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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