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 | ||
(e874-il) EPPLER 874 HYDROFOIL AIRFOIL | Eppler E874 hydrofoil Max thickness 7.9% at 28.8% chord Max camber 0.9% at 35.7% chord | Remove Airfoil details Airfoil plotter |
(e62-il) E62 (5.62%) | Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord Max camber 5% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e874-il,e62-il,c5d-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e874-il | 50,000 | 9 | 30.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e874-il | 50,000 | 5 | 29.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e874-il | 100,000 | 9 | 41.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e874-il | 100,000 | 5 | 40.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e874-il | 200,000 | 9 | 51.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e874-il | 200,000 | 5 | 49.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e874-il | 500,000 | 9 | 65.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e874-il | 500,000 | 5 | 60.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e874-il | 1,000,000 | 9 | 75 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e874-il | 1,000,000 | 5 | 63.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 50,000 | 9 | 48 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 50,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 100,000 | 9 | 74.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 100,000 | 5 | 74.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 200,000 | 9 | 107.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 200,000 | 5 | 104.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 500,000 | 9 | 156.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 500,000 | 5 | 141.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 9 | 191.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e62-il | 1,000,000 | 5 | 164.6 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 50,000 | 9 | 30.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 50,000 | 5 | 31 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 100,000 | 9 | 48.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 100,000 | 5 | 44.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 200,000 | 9 | 66.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 200,000 | 5 | 53.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 500,000 | 9 | 75.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 500,000 | 5 | 62.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 1,000,000 | 9 | 79.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 1,000,000 | 5 | 78.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||