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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(e553-il) EPPLER 553 AIRFOIL | Eppler E553 general aviation airfoil Max thickness 18.1% at 31.8% chord Max camber 2.9% at 56.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e553-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e553-il | 50,000 | 9 | 4.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 50,000 | 5 | 17.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 100,000 | 9 | 45.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 100,000 | 5 | 49.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 200,000 | 9 | 71.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 200,000 | 5 | 69.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 500,000 | 9 | 99.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 500,000 | 5 | 93.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 9 | 121.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e553-il | 1,000,000 | 5 | 111.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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