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 |
(e664-il) EPPLER 664 AIRFOIL | Eppler E664 variable geometry sailplane airfoil Max thickness 16.6% at 45.6% chord Max camber 2.6% at 40.7% chord | Remove Airfoil details Airfoil plotter |
(e838-il) EPPLER E838 HYDROFOIL AIRFOIL | Eppler E838 hydrofoil Max thickness 18.4% at 37.2% chord Max camber 0% at 46.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e851-il,e664-il,e838-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 | |
| e664-il | 50,000 | 9 | 19.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 50,000 | 5 | 19.7 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 100,000 | 9 | 39.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 100,000 | 5 | 33.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 200,000 | 9 | 57.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 200,000 | 5 | 58.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 500,000 | 9 | 90.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 500,000 | 5 | 90.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 9 | 120.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 5 | 111.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 50,000 | 9 | 18.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 50,000 | 5 | 16.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 100,000 | 9 | 31.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 100,000 | 5 | 29.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 200,000 | 9 | 51.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 200,000 | 5 | 49.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 500,000 | 9 | 73.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 500,000 | 5 | 65 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 9 | 86.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e838-il | 1,000,000 | 5 | 72.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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