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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(e337-il) EPPLER 337 AIRFOIL | Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e337-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e337-il | 50,000 | 9 | 16 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 100,000 | 9 | 34.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 100,000 | 5 | 45.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 200,000 | 9 | 62.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 200,000 | 5 | 65.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 500,000 | 9 | 92.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 500,000 | 5 | 84.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 9 | 107.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e337-il | 1,000,000 | 5 | 103.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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