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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(e385-il) E385 (8.41%) | Eppler E385 airfoil Max thickness 8.4% at 29.6% chord Max camber 5.3% at 47.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e385-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e385-il | 50,000 | 9 | 38.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e385-il | 50,000 | 5 | 39.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e385-il | 100,000 | 9 | 67.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e385-il | 100,000 | 5 | 68.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e385-il | 200,000 | 9 | 96.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e385-il | 200,000 | 5 | 96.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e385-il | 500,000 | 9 | 139 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e385-il | 500,000 | 5 | 133.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e385-il | 1,000,000 | 9 | 172.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e385-il | 1,000,000 | 5 | 159.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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