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 | ||
(goe517-il) GOE 517 AIRFOIL | Gottingen 517 airfoil Max thickness 7% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe517-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe517-il | 50,000 | 9 | 37.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 50,000 | 5 | 40.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 9 | 55.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 100,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 9 | 75 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 200,000 | 5 | 79.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 9 | 103 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 500,000 | 5 | 102 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 9 | 121.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe517-il | 1,000,000 | 5 | 117.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||