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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(e1214-il) EPPLER 1214 AIRFOIL | Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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