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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(e207-il) E207 (12.04%) | Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e207-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e207-il | 50,000 | 9 | 30.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 50,000 | 5 | 32.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 100,000 | 9 | 52.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 100,000 | 5 | 53.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 200,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 200,000 | 5 | 72.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 500,000 | 9 | 102.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 500,000 | 5 | 96.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e207-il | 1,000,000 | 9 | 124.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e207-il | 1,000,000 | 5 | 112.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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