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 | ||
(goe405-il) GOE 405 AIRFOIL | Gottingen 405 airfoil Max thickness 11.1% at 30% chord Max camber 6.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe780-il) GOE 780 AIRFOIL | Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe533-il) GOE 533 AIRFOIL | Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe405-il,goe780-il,goe533-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe405-il | 50,000 | 9 | 9.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 50,000 | 5 | 29.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 9 | 54.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 5 | 58.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 9 | 82.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 5 | 80.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 9 | 115.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 5 | 104.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 9 | 137.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 5 | 126.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 9 | 12.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 5 | 19.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 9 | 29.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 9 | 44.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 5 | 34.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 9 | 42.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 5 | 42.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 9 | 50.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 5 | 44 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 50,000 | 9 | 10.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 50,000 | 5 | 29.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 100,000 | 9 | 46.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 100,000 | 5 | 54.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 200,000 | 9 | 73.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 200,000 | 5 | 75.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 500,000 | 9 | 106.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 500,000 | 5 | 102.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe533-il | 1,000,000 | 9 | 131.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe533-il | 1,000,000 | 5 | 121.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||