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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(s1210-il) S1210 12% | Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s1210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1210-il | 50,000 | 9 | 14.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 50,000 | 5 | 42.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 9 | 59.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 5 | 66 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 5 | 88 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 9 | 121.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 5 | 115 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 9 | 148 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 5 | 135.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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