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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(e209-il) E209 (13.72%) | Eppler E209 low Reynolds number airfoil Max thickness 13.7% at 33.8% chord Max camber 1.6% at 48.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e209-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e209-il | 50,000 | 9 | 29.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 50,000 | 5 | 31.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 100,000 | 9 | 50.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 100,000 | 5 | 51.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 200,000 | 9 | 71.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 200,000 | 5 | 69.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 500,000 | 9 | 100.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 500,000 | 5 | 93 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e209-il | 1,000,000 | 9 | 121.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e209-il | 1,000,000 | 5 | 103.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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