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 | ||
(goe155-il) GOE 155 (SSW D.1) AIRFOIL | Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe155-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe155-il | 50,000 | 9 | 40.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 9 | 59.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 9 | 82.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 5 | 78.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 9 | 107.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 5 | 98.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 5 | 111 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||