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 | ||
(goe505-il) GOE 505 AIRFOIL | Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe434-il) GOE 434 AIRFOIL | Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord | Remove Airfoil details Airfoil plotter |
(goe190-il) GOE 190 (MVA MK.18) AIRFOIL | Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe505-il,goe434-il,goe190-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe505-il | 50,000 | 9 | 12.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 50,000 | 5 | 29.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 100,000 | 9 | 49.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 100,000 | 5 | 43.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 200,000 | 9 | 68.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 200,000 | 5 | 53.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 500,000 | 9 | 73.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 500,000 | 5 | 69.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe505-il | 1,000,000 | 9 | 91 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe505-il | 1,000,000 | 5 | 87.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 50,000 | 9 | 3.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 50,000 | 5 | 11.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 100,000 | 9 | 36 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 100,000 | 5 | 36.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 200,000 | 9 | 65.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 200,000 | 5 | 62.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 500,000 | 9 | 94.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 500,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe434-il | 1,000,000 | 9 | 110.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe434-il | 1,000,000 | 5 | 93.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe190-il | 50,000 | 9 | 15.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe190-il | 50,000 | 5 | 37.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe190-il | 100,000 | 9 | 52.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe190-il | 100,000 | 5 | 57.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe190-il | 200,000 | 9 | 77.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe190-il | 200,000 | 5 | 74.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe190-il | 500,000 | 9 | 100.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe190-il | 500,000 | 5 | 97 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe190-il | 1,000,000 | 9 | 121.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe190-il | 1,000,000 | 5 | 114.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||