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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(e559-il) EPPLER 559 AIRFOIL | Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord | Remove Airfoil details Airfoil plotter |
(e557-il) EPPLER 557 AIRFOIL | Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord | Remove Airfoil details Airfoil plotter |
(e593-il) EPPLER 593 AIRFOIL | Eppler E593 airfoil Max thickness 11.3% at 24.2% chord Max camber 4.6% at 29.2% chord | Remove Airfoil details Airfoil plotter |
(e558-il) EPPLER 558 AIRFOIL | Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(e582-il) EPPLER 582 AIRFOIL | Eppler E582 sailplane airfoil Max thickness 14.7% at 37.8% chord Max camber 4.2% at 43.1% chord | Remove Airfoil details Airfoil plotter |
(e59-il) EPPLER 59 AIRFOIL | Eppler E59 low Reynolds number airfoil Max thickness 5.6% at 25% chord Max camber 5.2% at 50% chord | Remove Airfoil details Airfoil plotter |
(e587-il) EPPLER 587 AIRFOIL | Eppler E587 sailplane airfoil Max thickness 16.6% at 41.1% chord Max camber 4.2% at 51.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e559-il,e557-il,e593-il,e558-il,e582-il,e59-il,e587-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e559-il | 50,000 | 9 | 8.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 50,000 | 5 | 30.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 100,000 | 9 | 43.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 100,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 200,000 | 9 | 70.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 200,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 500,000 | 5 | 101.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 9 | 130.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 5 | 123.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 50,000 | 9 | 25.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 50,000 | 5 | 32.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 100,000 | 9 | 53.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 100,000 | 5 | 54.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 200,000 | 9 | 75 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 200,000 | 5 | 73.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 500,000 | 5 | 95.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 9 | 122.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 50,000 | 9 | 7.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 50,000 | 5 | 16.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 100,000 | 9 | 25 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 100,000 | 5 | 36.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 200,000 | 9 | 71.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 200,000 | 5 | 74.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 500,000 | 9 | 115.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 500,000 | 5 | 113.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 9 | 148.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 5 | 140.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 50,000 | 9 | 9.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 50,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 100,000 | 9 | 41.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 200,000 | 9 | 67.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 200,000 | 5 | 70.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 500,000 | 9 | 100.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 500,000 | 5 | 99.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 9 | 127 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 5 | 120.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 50,000 | 9 | 7.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 50,000 | 5 | 20.7 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 100,000 | 9 | 47.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 100,000 | 5 | 45.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 200,000 | 9 | 78 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 200,000 | 5 | 75 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 500,000 | 9 | 112 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 500,000 | 5 | 106.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e582-il | 1,000,000 | 9 | 140.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e582-il | 1,000,000 | 5 | 128.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 50,000 | 9 | 43.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 50,000 | 5 | 46.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 100,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 100,000 | 5 | 70.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 200,000 | 9 | 103.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 200,000 | 5 | 99.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 500,000 | 9 | 155.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 500,000 | 5 | 119.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 9 | 188.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 5 | 108.8 at α=-1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 50,000 | 9 | 7.3 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 50,000 | 5 | 18.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 100,000 | 9 | 44.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 100,000 | 5 | 41.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 200,000 | 9 | 75.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 200,000 | 5 | 75.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 500,000 | 9 | 116.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 500,000 | 5 | 110 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e587-il | 1,000,000 | 9 | 145.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e587-il | 1,000,000 | 5 | 131.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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