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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(e561-il) EPPLER 561 AIRFOIL | Eppler E561 general aviation airfoil Max thickness 16.9% at 27.9% chord Max camber 5.1% at 45.8% 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 |
(e603-il) EPPLER 603 AIRFOIL | Eppler E603 general purpose airfoil Max thickness 19% at 40% chord Max camber 3.6% at 35.6% 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 |
(e58-il) EPPLER 58 AIRFOIL | Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e561-il,e582-il,e603-il,e587-il,e58-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e561-il | 50,000 | 9 | 5.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 50,000 | 5 | 26.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 100,000 | 9 | 39.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 100,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 200,000 | 9 | 70 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 200,000 | 5 | 74.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 500,000 | 9 | 105 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 500,000 | 5 | 104.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e561-il | 1,000,000 | 9 | 134.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e561-il | 1,000,000 | 5 | 128.3 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 | |
| e603-il | 50,000 | 9 | 4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 50,000 | 5 | 10.2 at α=15.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 100,000 | 9 | 26.6 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 100,000 | 5 | 22.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 200,000 | 9 | 56.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 200,000 | 5 | 63 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 500,000 | 9 | 103.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 500,000 | 5 | 103.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e603-il | 1,000,000 | 9 | 136.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e603-il | 1,000,000 | 5 | 127.8 at α=6° | 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 | |
| e58-il | 50,000 | 9 | 46.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 50,000 | 5 | 44.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 100,000 | 9 | 70.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 100,000 | 5 | 68.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 200,000 | 9 | 108.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 200,000 | 5 | 106.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 500,000 | 9 | 175.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 500,000 | 5 | 166.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 9 | 235.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e58-il | 1,000,000 | 5 | 160.8 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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