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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(e174-il) E174 (Dicke 8.92%) | Eppler E174 low Reynolds number airfoil Max thickness 8.9% at 31.2% chord Max camber 3.3% at 44.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e174-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e174-il | 50,000 | 9 | 38.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 50,000 | 5 | 39 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 100,000 | 9 | 61.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 100,000 | 5 | 61.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 200,000 | 9 | 84.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 200,000 | 5 | 83 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 500,000 | 9 | 117.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 500,000 | 5 | 110.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e174-il | 1,000,000 | 9 | 141.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e174-il | 1,000,000 | 5 | 128.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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