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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(e851-il) EPPLER E851 AIRFOIL | Eppler E851 propeller airfoil Max thickness 9% at 37% chord Max camber 2.3% at 66.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e851-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e851-il | 50,000 | 9 | 27.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 50,000 | 5 | 31 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 100,000 | 9 | 49 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 100,000 | 5 | 50.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 200,000 | 9 | 77.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 200,000 | 5 | 73.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 500,000 | 9 | 110.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 500,000 | 5 | 90.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 9 | 122.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e851-il | 1,000,000 | 5 | 95.7 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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