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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(e638-il) EPPLER 638 AIRFOIL | Eppler E638 airfoil Max thickness 12.4% at 28.5% chord Max camber 4.4% at 24.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e638-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e638-il | 50,000 | 9 | 14.4 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 50,000 | 5 | 25.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 100,000 | 9 | 32.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 100,000 | 5 | 45.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 200,000 | 9 | 62.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 200,000 | 5 | 68.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 500,000 | 9 | 99.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 500,000 | 5 | 100.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 9 | 129.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e638-il | 1,000,000 | 5 | 126 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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