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 | ||
(goe123-il) GOE 123 AIRFOIL | Gottingen 123 airfoil Max thickness 5.4% at 25% chord Max camber 5.7% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe123-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe123-il | 50,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 50,000 | 5 | 45.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 100,000 | 9 | 65.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 100,000 | 5 | 66.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 200,000 | 9 | 92 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 200,000 | 5 | 85 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 500,000 | 9 | 118.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 500,000 | 5 | 102.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe123-il | 1,000,000 | 9 | 129.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe123-il | 1,000,000 | 5 | 110.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||