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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(e662-il) EPPLER E662 AIRFOIL | Eppler E662 sailplane airfoil Max thickness 15% at 42.8% chord Max camber 4.1% at 47.5% chord | Remove Airfoil details Airfoil plotter |
(e66-il) EPPLER 66 AIRFOIL | Eppler E66 low Reynolds number airfoil Max thickness 10.1% at 28.7% chord Max camber 4.1% at 52.3% chord | Remove Airfoil details Airfoil plotter |
(e62-il) E62 (5.62%) | Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord Max camber 5% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(e61-il) E61 (5.64%) | Eppler E61 low Reynolds number airfoil Max thickness 5.7% at 23.8% chord Max camber 6.4% at 51% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e662-il,e66-il,e62-il,e61-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e662-il | 50,000 | 9 | 27.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 50,000 | 5 | 23.4 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 100,000 | 9 | 46.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 100,000 | 5 | 40.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 200,000 | 9 | 71.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 200,000 | 5 | 66.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 500,000 | 9 | 114.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 500,000 | 5 | 111.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 9 | 152 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e662-il | 1,000,000 | 5 | 138.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 50,000 | 9 | 40.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 50,000 | 5 | 40.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 100,000 | 9 | 64.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 100,000 | 5 | 63.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 200,000 | 9 | 91.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 200,000 | 5 | 86.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 500,000 | 9 | 128.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 500,000 | 5 | 113.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 9 | 153.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e66-il | 1,000,000 | 5 | 121.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 50,000 | 9 | 48 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 50,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 100,000 | 9 | 74.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 100,000 | 5 | 74.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 200,000 | 9 | 107.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 200,000 | 5 | 104.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 500,000 | 9 | 156.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 500,000 | 5 | 141.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 9 | 191.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 5 | 164.6 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 50,000 | 9 | 46.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 50,000 | 5 | 45.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 100,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 100,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 200,000 | 9 | 112.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 200,000 | 5 | 110.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 500,000 | 9 | 171 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 500,000 | 5 | 157.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 9 | 214.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 5 | 176.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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