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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(e485-il) EPPLER 485 AIRFOIL | Eppler E485 tailplane airfoil Max thickness 12.5% at 31.8% chord Max camber 1.1% at 27.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e485-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e485-il | 50,000 | 9 | 27.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 50,000 | 5 | 30.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 100,000 | 9 | 44.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 100,000 | 5 | 44.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 200,000 | 9 | 59.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 200,000 | 5 | 55.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 500,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 500,000 | 5 | 69 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e485-il | 1,000,000 | 9 | 86.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e485-il | 1,000,000 | 5 | 81.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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