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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(e636-il) EPPLER 636 AIRFOIL | Eppler E636 airfoil Max thickness 11.9% at 26.9% chord Max camber 3.2% at 22.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e636-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e636-il | 50,000 | 9 | 14.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 50,000 | 5 | 24.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 100,000 | 9 | 33 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 100,000 | 5 | 44 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 200,000 | 9 | 61.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 500,000 | 9 | 95.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 500,000 | 5 | 94.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 9 | 120.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e636-il | 1,000,000 | 5 | 108.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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