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 | ||
(goe614-il) GOE 614 AIRFOIL | Gottingen 614 airfoil Max thickness 18.8% at 29.2% chord Max camber 6.2% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(goe420-il) GOE 420 AIRFOIL | Gottingen 420 airfoil Max thickness 18.8% at 30% chord Max camber 4.3% 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 |
Drawing Options
Polars for (goe614-il,goe420-il,goe575-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe614-il | 50,000 | 9 | 3.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 50,000 | 5 | 16.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 9 | 33.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 100,000 | 5 | 43.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 9 | 63.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 200,000 | 5 | 59.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 9 | 84.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 500,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 9 | 105.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe614-il | 1,000,000 | 5 | 79.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 50,000 | 9 | 4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 50,000 | 5 | 13.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 9 | 32.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 5 | 44.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 9 | 66.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 5 | 62.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 9 | 89.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 5 | 83.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 9 | 111.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 5 | 102.2 at α=7° | 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 | |
| Reynolds number calculator | |||||||