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 | ||
(goe321-il) GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL | Gottingen 321 (Hansa-Brandenburg III.1) airfoil Max thickness 11.2% at 29.9% chord Max camber 5.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe321-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe321-il | 50,000 | 9 | 20.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe321-il | 50,000 | 5 | 34.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe321-il | 100,000 | 9 | 54.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe321-il | 100,000 | 5 | 55.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe321-il | 200,000 | 9 | 77.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe321-il | 200,000 | 5 | 73.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe321-il | 500,000 | 9 | 105.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe321-il | 500,000 | 5 | 90.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe321-il | 1,000,000 | 9 | 120.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe321-il | 1,000,000 | 5 | 104.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||