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 | ||
(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 (goe190-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |||||||