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 | ||
(goe612-il) GOE 612 AIRFOIL | Gottingen 612 airfoil Max thickness 15% at 29.5% chord Max camber 5% at 49.5% chord | Remove Airfoil details Airfoil plotter |
(goe602m-il) GOE 602 MOD. AIRFOIL | Gottingen 602 MOD airfoil Max thickness 9.6% at 30% chord Max camber 3.8% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe575-il) GOE 575 AIRFOIL | Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(goe604-il) GOE 604 AIRFOIL | Gottingen 604 airfoil Max thickness 17.8% at 29.3% chord Max camber 5.4% at 29.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe612-il,goe602m-il,goe575-il,goe604-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe612-il | 50,000 | 9 | 9.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 50,000 | 5 | 27.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 9 | 51.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 100,000 | 5 | 49.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 200,000 | 5 | 70.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 9 | 105.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 500,000 | 5 | 85.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 9 | 121.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe612-il | 1,000,000 | 5 | 100 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 50,000 | 9 | 39.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 50,000 | 5 | 40.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 100,000 | 9 | 59.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 100,000 | 5 | 59.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 200,000 | 9 | 80 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 200,000 | 5 | 76.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 500,000 | 9 | 105.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 500,000 | 5 | 95.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602m-il | 1,000,000 | 9 | 122.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602m-il | 1,000,000 | 5 | 108.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 9 | 31.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 5 | 32.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 9 | 47.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 5 | 44.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 9 | 57.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 9 | 74.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 5 | 70.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 9 | 88.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 50,000 | 9 | 3.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 50,000 | 5 | 20.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 9 | 29.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 5 | 42.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 9 | 59.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 5 | 61.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 9 | 87.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 5 | 85.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 9 | 113 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||