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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(e343-il) EPPLER 343 AIRFOIL | Eppler E343 flying wing airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 26% chord | Remove Airfoil details Airfoil plotter |
(e377m-il) EPPLER 377 (MODIFIED) AIRFOIL | Eppler E377 (modified) ultralight airfoil Max thickness 3.8% at 6.1% chord Max camber 9.2% at 32.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e343-il,e377m-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e343-il | 50,000 | 9 | 14.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 50,000 | 5 | 24.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 100,000 | 9 | 30.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 100,000 | 5 | 43.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 200,000 | 9 | 58.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 200,000 | 5 | 64.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 500,000 | 9 | 92.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 500,000 | 5 | 87.9 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e343-il | 1,000,000 | 9 | 114.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e343-il | 1,000,000 | 5 | 113.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 50,000 | 9 | 17.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 50,000 | 5 | 36.8 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 100,000 | 9 | 61.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 100,000 | 5 | 63.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 200,000 | 9 | 86.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 200,000 | 5 | 86.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 500,000 | 9 | 117.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 500,000 | 5 | 115.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e377m-il | 1,000,000 | 9 | 142.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e377m-il | 1,000,000 | 5 | 137 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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