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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(e583-il) EPPLER 583 AIRFOIL | Eppler E583 sailplane airfoil Max thickness 16.5% at 38% chord Max camber 4.5% at 38% chord | Remove Airfoil details Airfoil plotter |
(e656-il) EPPLER 656 AIRFOIL | Eppler E656 sailplane airfoil Max thickness 16.2% at 37% chord Max camber 4.8% at 42.2% chord | Remove Airfoil details Airfoil plotter |
(s2062-il) S2062 8% | Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e583-il,e656-il,s2062-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e583-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e583-il | 50,000 | 5 | 11.5 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e583-il | 100,000 | 9 | 32.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e583-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e583-il | 200,000 | 9 | 70.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e583-il | 200,000 | 5 | 70 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e583-il | 500,000 | 9 | 111.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e583-il | 500,000 | 5 | 107.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e583-il | 1,000,000 | 9 | 143.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e583-il | 1,000,000 | 5 | 132 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 50,000 | 9 | 5.7 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 50,000 | 5 | 14.6 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 100,000 | 9 | 34.7 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 100,000 | 5 | 29.8 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 200,000 | 9 | 69.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 200,000 | 5 | 70.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 500,000 | 9 | 125.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 500,000 | 5 | 118.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 9 | 161.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e656-il | 1,000,000 | 5 | 147.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2062-il | 50,000 | 9 | 36 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2062-il | 50,000 | 5 | 36.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2062-il | 100,000 | 9 | 52.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2062-il | 100,000 | 5 | 49.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2062-il | 200,000 | 9 | 69.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2062-il | 200,000 | 5 | 61.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2062-il | 500,000 | 9 | 89.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2062-il | 500,000 | 5 | 74.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2062-il | 1,000,000 | 9 | 99.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2062-il | 1,000,000 | 5 | 78.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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