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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(e855-il) EPPLER 855 AIRFOIL | Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord Max camber 3.7% at 50.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e855-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e855-il | 50,000 | 9 | 5.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 50,000 | 5 | 23 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 100,000 | 9 | 47 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 100,000 | 5 | 52.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 200,000 | 9 | 76.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 200,000 | 5 | 77.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 500,000 | 9 | 112 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 500,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 9 | 140.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e855-il | 1,000,000 | 5 | 122.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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