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 | ||
(goe575-il) GOE 575 AIRFOIL | Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe575-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe575-il | 50,000 | 9 | 31.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 5 | 32.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 9 | 47.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 5 | 44.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 9 | 57.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 9 | 74.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 5 | 70.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 9 | 88.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||