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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(e210-il) E210 (13.64%) | Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e210-il | 50,000 | 9 | 9.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 100,000 | 9 | 52.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 100,000 | 5 | 57.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 200,000 | 9 | 78.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 200,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 500,000 | 9 | 113 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 500,000 | 5 | 109 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 9 | 140.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 5 | 129.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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