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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(e395-il) EPPLER 395 AIRFOIL | Eppler E395 human e664ered aircraft airfoil Max thickness 12.3% at 29.5% chord Max camber 5.2% at 52.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e395-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e395-il | 50,000 | 9 | 31 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 50,000 | 5 | 28.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 100,000 | 9 | 59.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 100,000 | 5 | 61.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 200,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 200,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 500,000 | 9 | 136.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 500,000 | 5 | 128.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 9 | 169.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e395-il | 1,000,000 | 5 | 144.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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