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 | ||
(goe673-il) GOE 673 AIRFOIL | Gottingen 673 airfoil Max thickness 10.8% at 29.7% chord Max camber 2.8% at 49.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe673-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe673-il | 50,000 | 9 | 38.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 50,000 | 5 | 37.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 100,000 | 9 | 56 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 100,000 | 5 | 55.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 200,000 | 9 | 75 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 200,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 500,000 | 9 | 100.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 500,000 | 5 | 94.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe673-il | 1,000,000 | 9 | 118.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe673-il | 1,000,000 | 5 | 109.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||