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 | ||
(goe227-il) GOE 227 (MVA H.37) AIRFOIL | Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe227-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe227-il | 50,000 | 9 | 7.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 50,000 | 5 | 23.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 100,000 | 9 | 49.6 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 100,000 | 5 | 58.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 200,000 | 9 | 88 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 200,000 | 5 | 88.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 500,000 | 9 | 131.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 500,000 | 5 | 118.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe227-il | 1,000,000 | 9 | 155.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe227-il | 1,000,000 | 5 | 134.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||