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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(e397-il) EPPLER 397 AIRFOIL | Eppler E397 human powered aircraft airfoil Max thickness 13.5% at 29.4% chord Max camber 5.3% at 52.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e397-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e397-il | 50,000 | 9 | 26.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e397-il | 50,000 | 5 | 22.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e397-il | 100,000 | 9 | 51 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e397-il | 100,000 | 5 | 53.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e397-il | 200,000 | 9 | 89 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e397-il | 200,000 | 5 | 89.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e397-il | 500,000 | 9 | 135.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e397-il | 500,000 | 5 | 126 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e397-il | 1,000,000 | 9 | 169.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e397-il | 1,000,000 | 5 | 139.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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