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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(e479-il) EPPLER 479 AIRFOIL | Eppler E479 aerobatic aircraft airfoil Max thickness 16.6% at 25.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e479-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e479-il | 50,000 | 9 | 15.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 50,000 | 5 | 23.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 100,000 | 9 | 33.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 100,000 | 5 | 39 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 200,000 | 9 | 52.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 200,000 | 5 | 54.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 500,000 | 9 | 76.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 500,000 | 5 | 74.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 9 | 95.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e479-il | 1,000,000 | 5 | 88.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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