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 | ||
(goe549-il) GOE 549 AIRFOIL | Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe549-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe549-il | 50,000 | 9 | 7.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 50,000 | 5 | 26.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 100,000 | 9 | 43 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 100,000 | 5 | 52.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 200,000 | 9 | 74.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 200,000 | 5 | 75.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 500,000 | 9 | 107.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 500,000 | 5 | 100.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 1,000,000 | 9 | 128.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 1,000,000 | 5 | 115.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||