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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(goe600-il) GOE 600 AIRFOIL | Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe600-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe600-il | 50,000 | 9 | 32.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 5 | 33.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 5 | 49.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 9 | 69.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 5 | 62.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 9 | 91.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 9 | 99.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 5 | 86 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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