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 |
(goe529-il) GOE 529 AIRFOIL | Gottingen 529 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe531-il,goe529-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 | |
| goe529-il | 50,000 | 9 | 12.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 50,000 | 5 | 33.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 100,000 | 9 | 54.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 100,000 | 5 | 60 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 200,000 | 9 | 81.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 200,000 | 5 | 81.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 500,000 | 9 | 114.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 500,000 | 5 | 109 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe529-il | 1,000,000 | 9 | 138.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe529-il | 1,000,000 | 5 | 127.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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