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 | ||
(e169-il) E169 (14.4%) | Eppler E169 low Reynolds number airfoil Max thickness 14.4% at 26.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca66210-il) NACA 66-210 | NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e169-il,naca66210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e169-il | 50,000 | 9 | 16.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 50,000 | 5 | 27 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 100,000 | 9 | 39.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 100,000 | 5 | 41.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 200,000 | 9 | 56.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 200,000 | 5 | 55.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 500,000 | 9 | 77.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 500,000 | 5 | 71.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 1,000,000 | 9 | 92.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 1,000,000 | 5 | 79.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 9 | 22.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 50,000 | 5 | 27.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 100,000 | 5 | 36.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 9 | 51.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 200,000 | 5 | 46.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 5 | 61.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca66210-il | 500,000 | 0 | 67.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 9 | 82.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca66210-il | 1,000,000 | 5 | 67.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||