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 | ||
(goe11k-il) GOE 11K AIRFOIL | Gottingen 11K airfoil Max thickness 7.5% at 50% chord Max camber 2.7% at 60% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe11k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe11k-il | 50,000 | 9 | 28.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 50,000 | 5 | 31.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 9 | 41.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 100,000 | 5 | 49 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 9 | 72.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 200,000 | 5 | 72.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 9 | 109.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 500,000 | 5 | 99.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 9 | 122.4 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe11k-il | 1,000,000 | 5 | 87.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||