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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(e184-il) E184 (8.33%) | Eppler E184 low Reynolds number airfoil Max thickness 8.3% at 33.3% chord Max camber 0.8% at 38.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e184-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e184-il | 50,000 | 9 | 30.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e184-il | 50,000 | 5 | 31.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e184-il | 100,000 | 9 | 44.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e184-il | 100,000 | 5 | 43.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e184-il | 200,000 | 9 | 58 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e184-il | 200,000 | 5 | 53.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e184-il | 500,000 | 9 | 73.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e184-il | 500,000 | 5 | 63.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e184-il | 1,000,000 | 9 | 82.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e184-il | 1,000,000 | 5 | 67 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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