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 | ||
(goe427-il) GOE 427 AIRFOIL | Gottingen 427 airfoil Max thickness 4.6% at 20% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe427-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe427-il | 50,000 | 9 | 45.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 50,000 | 5 | 46.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 9 | 66.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 5 | 67.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 9 | 89 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 5 | 86.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 9 | 114.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 5 | 94.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 9 | 122.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 5 | 95 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||