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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(e542-il) EPPLER 542 AIRFOIL | Eppler E542 general aviation airfoil Max thickness 16.9% at 41.3% chord Max camber 1.9% at 31.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e542-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e542-il | 50,000 | 9 | 6.9 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e542-il | 50,000 | 5 | 18.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e542-il | 100,000 | 9 | 47.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e542-il | 100,000 | 5 | 32.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e542-il | 200,000 | 9 | 52.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e542-il | 200,000 | 5 | 54.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e542-il | 500,000 | 9 | 79.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e542-il | 500,000 | 5 | 78.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e542-il | 1,000,000 | 9 | 102.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e542-il | 1,000,000 | 5 | 94 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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