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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(e857-il) EPPLER 857 AIRFOIL | Eppler E857 propeller airfoil Max thickness 20.3% at 31.5% chord Max camber 4.9% at 45.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e857-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e857-il | 50,000 | 9 | 3.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e857-il | 50,000 | 5 | 16 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e857-il | 100,000 | 9 | 25.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e857-il | 100,000 | 5 | 41.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e857-il | 200,000 | 9 | 56.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e857-il | 200,000 | 5 | 62.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e857-il | 500,000 | 9 | 88.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e857-il | 500,000 | 5 | 85.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e857-il | 1,000,000 | 9 | 110.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e857-il | 1,000,000 | 5 | 105.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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