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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(e635-il) EPPLER 635 AIRFOIL | Eppler E635 airfoil Max thickness 11.6% at 26.2% chord Max camber 2.9% at 22.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e635-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e635-il | 50,000 | 9 | 14.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 50,000 | 5 | 24 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 100,000 | 9 | 36.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 100,000 | 5 | 43.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 200,000 | 9 | 60.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 200,000 | 5 | 64 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 500,000 | 9 | 92.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 500,000 | 5 | 88 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 9 | 113.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e635-il | 1,000,000 | 5 | 100 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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