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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(e547-il) EPPLER 547 AIRFOIL | Eppler E547 general aviation airfoil Max thickness 17.4% at 40.3% chord Max camber 2% at 30.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e547-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e547-il | 50,000 | 9 | 6.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 50,000 | 5 | 15 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 100,000 | 9 | 41.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 100,000 | 5 | 41 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 200,000 | 9 | 61.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 200,000 | 5 | 62 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 500,000 | 9 | 90.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 500,000 | 5 | 85.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 9 | 111.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e547-il | 1,000,000 | 5 | 101.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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