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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(e584-il) EPPLER 584 AIRFOIL | Eppler E584 sailplane airfoil Max thickness 16.6% at 38.3% chord Max camber 4.5% at 38.3% chord | Remove Airfoil details Airfoil plotter |
(e591-il) E591 | Eppler E591 airfoil Max thickness 15.7% at 25% chord Max camber 6% at 52.3% chord | Remove Airfoil details Airfoil plotter |
(e585-il) EPPLER 585 AIRFOIL | Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e584-il,e591-il,e585-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e584-il | 50,000 | 9 | 4.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 50,000 | 5 | 11.9 at α=-1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 100,000 | 9 | 29.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 100,000 | 5 | 32.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 200,000 | 9 | 67.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 200,000 | 5 | 64.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 500,000 | 9 | 103.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 500,000 | 5 | 101.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e584-il | 1,000,000 | 9 | 134 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e584-il | 1,000,000 | 5 | 126.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 50,000 | 9 | 10 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 50,000 | 5 | 34.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 100,000 | 9 | 52.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 100,000 | 5 | 57.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 200,000 | 9 | 77.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 200,000 | 5 | 76.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 500,000 | 9 | 107.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 500,000 | 5 | 99.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e591-il | 1,000,000 | 9 | 129.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e591-il | 1,000,000 | 5 | 118.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 50,000 | 9 | 8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 50,000 | 5 | 21.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 100,000 | 5 | 47.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 200,000 | 9 | 81.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 200,000 | 5 | 78.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 500,000 | 9 | 118 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 500,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 9 | 146.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e585-il | 1,000,000 | 5 | 131.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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