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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(e216-il) E216 (10.4%) | Eppler E216 low Reynolds number airfoil Max thickness 10.4% at 26.2% chord Max camber 4.7% at 59% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e216-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e216-il | 50,000 | 9 | 40.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 50,000 | 5 | 43 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 100,000 | 9 | 68.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 100,000 | 5 | 68.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 200,000 | 9 | 99.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 200,000 | 5 | 94 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 500,000 | 9 | 136.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 500,000 | 5 | 115.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e216-il | 1,000,000 | 9 | 155.1 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e216-il | 1,000,000 | 5 | 127.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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