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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(e49-il) EPPLER 49 AIRFOIL | Eppler E49 low Reynolds number airfoil Max thickness 7.2% at 38.4% chord Max camber 6.5% at 62.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e49-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e49-il | 50,000 | 9 | 37.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e49-il | 50,000 | 5 | 34.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e49-il | 100,000 | 9 | 56.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e49-il | 100,000 | 5 | 50.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e49-il | 200,000 | 9 | 82.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e49-il | 200,000 | 5 | 65 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e49-il | 500,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e49-il | 1,000,000 | 9 | 155.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e49-il | 1,000,000 | 5 | 123.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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