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 | ||
(e182-il) E182 (8.47%) | Eppler E182 low Reynolds number airfoil Max thickness 8.5% at 32.4% chord Max camber 1.2% at 37.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e182-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e182-il | 50,000 | 9 | 32.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 50,000 | 5 | 34.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 100,000 | 9 | 48.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 100,000 | 5 | 47 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 200,000 | 9 | 64.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 200,000 | 5 | 58.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 500,000 | 9 | 81.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 500,000 | 5 | 71.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e182-il | 1,000,000 | 9 | 92.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e182-il | 1,000,000 | 5 | 78.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||