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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(e858-il) EPPLER 858 AIRFOIL | Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e858-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e858-il | 50,000 | 9 | 3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 50,000 | 5 | 13 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 100,000 | 9 | 21.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 100,000 | 5 | 34.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 200,000 | 9 | 48.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 200,000 | 5 | 51.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 500,000 | 9 | 73.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 500,000 | 5 | 67.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e858-il | 1,000,000 | 9 | 88.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e858-il | 1,000,000 | 5 | 87.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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