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 | ||
(goe632-il) GOE 632 AIRFOIL | Gottingen 632 airfoil Max thickness 14% at 30% chord Max camber 3.9% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe632-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe632-il | 50,000 | 9 | 7.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 50,000 | 5 | 26 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 100,000 | 9 | 48.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 100,000 | 5 | 51.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 200,000 | 9 | 72.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 200,000 | 5 | 69.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 500,000 | 9 | 98.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 500,000 | 5 | 81.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe632-il | 1,000,000 | 9 | 104.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe632-il | 1,000,000 | 5 | 88.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||