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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(e180-il) E180 (8.59%) | Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e180-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e180-il | 50,000 | 9 | 35.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 50,000 | 5 | 36.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 100,000 | 9 | 52.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 100,000 | 5 | 51.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 200,000 | 9 | 71 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 200,000 | 5 | 66 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 500,000 | 9 | 93.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 500,000 | 5 | 82.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e180-il | 1,000,000 | 9 | 109.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e180-il | 1,000,000 | 5 | 91.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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