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 | ||
(goe620-il) GOE 620 AIRFOIL | Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe620-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe620-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 50,000 | 5 | 14.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 5 | 43.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 9 | 71.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 5 | 64.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 9 | 97.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 5 | 82.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 9 | 117.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 5 | 87.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||