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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(e541-il) EPPLER 541 AIRFOIL | Eppler E541 general aviation airfoil Max thickness 16.6% at 46.2% chord Max camber 1.7% at 36.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e541-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e541-il | 50,000 | 9 | 25.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 100,000 | 9 | 40.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 200,000 | 9 | 46.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 200,000 | 5 | 50.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 500,000 | 9 | 78.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 500,000 | 5 | 79.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e541-il | 1,000,000 | 9 | 106.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e541-il | 1,000,000 | 5 | 96.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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