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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(ec863914-il) EPPLER EC 86(-3)-914 AIRFOIL | Eppler EC 86(-3)-914 airfoil Max thickness 14.3% at 35.5% chord Max camber 4.4% at 71.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ec863914-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ec863914-il | 50,000 | 9 | 34.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 50,000 | 5 | 32.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 100,000 | 9 | 50.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 100,000 | 5 | 44.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 200,000 | 9 | 62.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 200,000 | 5 | 63 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 500,000 | 9 | 103.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 500,000 | 5 | 98.1 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ec863914-il | 1,000,000 | 9 | 150.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ec863914-il | 1,000,000 | 5 | 101 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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