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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(e1098-il) EPPLER 1098 AIRFOIL | Eppler E1098 general aviation airfoil Max thickness 18.9% at 36.6% chord Max camber 3.7% at 54.5% chord | Remove Airfoil details Airfoil plotter |
(e1200-il) EPPLER 1200 AIRFOIL | Eppler E1200 general aviation airfoil Max thickness 16.9% at 36.1% chord Max camber 3.5% at 50.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1098-il,e1200-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1098-il | 50,000 | 9 | 5.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 50,000 | 5 | 14.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 9 | 29.8 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 100,000 | 5 | 24.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 9 | 51.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 200,000 | 5 | 63.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 9 | 117.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 500,000 | 5 | 112.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 9 | 151.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1098-il | 1,000,000 | 5 | 139.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 50,000 | 9 | 9.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 50,000 | 5 | 23.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 100,000 | 9 | 46.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 100,000 | 5 | 39.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 200,000 | 9 | 69.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 200,000 | 5 | 68.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 500,000 | 5 | 96.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1200-il | 1,000,000 | 9 | 131.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1200-il | 1,000,000 | 5 | 109.4 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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