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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(e856-il) EPPLER 856 AIRFOIL | Eppler E856 propeller airfoil Max thickness 18.2% at 31.9% chord Max camber 4.2% at 50.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e856-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e856-il | 50,000 | 9 | 4.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 50,000 | 5 | 18.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 100,000 | 9 | 28.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 100,000 | 5 | 46.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 200,000 | 9 | 64.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 200,000 | 5 | 70.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 500,000 | 9 | 100.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 500,000 | 5 | 99.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e856-il | 1,000,000 | 9 | 128.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e856-il | 1,000,000 | 5 | 118.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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