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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(e639-il) EPPLER 639 AIRFOIL | Eppler E639 airfoil Max thickness 12.6% at 29.2% chord Max camber 4.8% at 29.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e639-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e639-il | 50,000 | 9 | 13.3 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 50,000 | 5 | 25.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 100,000 | 9 | 32.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 100,000 | 5 | 46 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 200,000 | 9 | 62.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 200,000 | 5 | 69.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 500,000 | 9 | 100.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 500,000 | 5 | 102.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e639-il | 1,000,000 | 9 | 131.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e639-il | 1,000,000 | 5 | 129.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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