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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(e555-il) EPPLER 555 AIRFOIL | Eppler E555 general aviation airfoil Max thickness 16% at 31.9% chord Max camber 2.6% at 67.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e555-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e555-il | 50,000 | 9 | 27.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 50,000 | 5 | 32.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 100,000 | 9 | 51.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 100,000 | 5 | 51.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 200,000 | 9 | 69.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 200,000 | 5 | 67.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 500,000 | 9 | 93.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 500,000 | 5 | 86.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 9 | 110.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 5 | 99.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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