Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(e598-il) EPPLER 598 AIRFOIL | Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord | Remove Airfoil details Airfoil plotter |
(goe613-il) GOE 613 AIRFOIL | Gottingen 613 airfoil Max thickness 10.3% at 30% chord Max camber 4.1% at 40% 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 |
Drawing Options
Polars for (e598-il,goe613-il,e593-il,e558-il,e582-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e598-il | 50,000 | 9 | 9.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 50,000 | 5 | 23.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 100,000 | 9 | 43.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 100,000 | 5 | 50.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 200,000 | 9 | 72.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 200,000 | 5 | 75.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 500,000 | 9 | 109.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 500,000 | 5 | 106.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 9 | 137.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 5 | 128.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 50,000 | 9 | 30.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 50,000 | 5 | 37 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 100,000 | 9 | 53.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 100,000 | 5 | 52.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 200,000 | 9 | 72.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 200,000 | 5 | 67.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 500,000 | 9 | 93.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 500,000 | 5 | 88.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe613-il | 1,000,000 | 9 | 112 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe613-il | 1,000,000 | 5 | 106 at α=4.75° | 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 | |
| Reynolds number calculator | |||||||