Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(goe531-il) GOE 531 AIRFOIL | Gottingen 531 airfoil Max thickness 13.8% at 19.5% chord Max camber 14.7% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(goe770-il) GOE 770 AIRFOIL | Gottingen 770 airfoil Max thickness 21% at 30% chord Max camber 4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe531-il,goe770-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe531-il | 50,000 | 9 | 4.2 at α=16.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 50,000 | 5 | 7.1 at α=18.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 9 | 7.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 100,000 | 5 | 9.9 at α=18.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 9 | 13.7 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 200,000 | 5 | 13.5 at α=17.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 9 | 67.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 500,000 | 5 | 66.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 9 | 100.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe531-il | 1,000,000 | 5 | 86.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 50,000 | 9 | 2.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 50,000 | 5 | 11.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 100,000 | 9 | 19.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 100,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 200,000 | 9 | 53.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 200,000 | 5 | 59.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 500,000 | 9 | 87.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 500,000 | 5 | 86.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe770-il | 1,000,000 | 9 | 112.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe770-il | 1,000,000 | 5 | 109 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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