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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(e186-il) E186 (10.27%) | Eppler E186 low Reynolds number airfoil Max thickness 10.2% at 29% chord Max camber 0.8% at 29% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e186-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e186-il | 50,000 | 9 | 29.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 50,000 | 5 | 31.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 100,000 | 9 | 46 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 100,000 | 5 | 45.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 200,000 | 9 | 61.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 200,000 | 5 | 58.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 500,000 | 9 | 79.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 500,000 | 5 | 71.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 1,000,000 | 9 | 90.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 1,000,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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