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 | ||
(goe304-il) GOE 304 (FRIEDRICHSHAFEN G02) AIRFOIL | Gottingen 304 (Friedrichshafen G02) airfoil Max thickness 9% at 29.8% chord Max camber 6.3% at 39.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe304-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe304-il | 50,000 | 9 | 33.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 50,000 | 5 | 38.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 100,000 | 9 | 62 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 100,000 | 5 | 64.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 200,000 | 9 | 88.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 200,000 | 5 | 86.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 500,000 | 9 | 122.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 500,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe304-il | 1,000,000 | 9 | 145.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe304-il | 1,000,000 | 5 | 117.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||