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 | ||
(goe391-il) GOE 391 AIRFOIL | Gottingen 391 airfoil Max thickness 5.1% at 40% chord Max camber 3.2% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe391-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe391-il | 50,000 | 9 | 39.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 50,000 | 5 | 41.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 100,000 | 9 | 58.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 100,000 | 5 | 58.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 200,000 | 5 | 75.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 200,000 | 0 | 84.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 500,000 | 9 | 106 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 500,000 | 5 | 84.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe391-il | 1,000,000 | 9 | 104.7 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe391-il | 1,000,000 | 5 | 86.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||