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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(e377-il) EPPLER 377 AIRFOIL | Eppler E377 ultralight airfoil Max thickness 3.9% at 8.4% chord Max camber 8.8% at 36.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e377-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e377-il | 50,000 | 9 | 32.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377-il | 50,000 | 5 | 38.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377-il | 100,000 | 9 | 104.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377-il | 100,000 | 5 | 66.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377-il | 200,000 | 9 | 91.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377-il | 200,000 | 5 | 94.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377-il | 500,000 | 9 | 133.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377-il | 500,000 | 5 | 130.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377-il | 1,000,000 | 9 | 167.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377-il | 1,000,000 | 5 | 141 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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