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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(e221-il) E221 (9.39%) | Eppler E221 low Reynolds number airfoil Max thickness 9.4% at 28.1% chord Max camber 1.6% at 32.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e221-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e221-il | 50,000 | 9 | 29.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 50,000 | 5 | 33.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 100,000 | 9 | 47 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 200,000 | 9 | 64.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 200,000 | 5 | 62.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 500,000 | 5 | 79.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e221-il | 1,000,000 | 9 | 100.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e221-il | 1,000,000 | 5 | 90.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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