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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(goe599-il) GOE 599 AIRFOIL | Gottingen 599 airfoil Max thickness 10% at 29.6% chord Max camber 1.5% at 59.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe599-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe599-il | 50,000 | 9 | 34.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 50,000 | 5 | 33.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 100,000 | 9 | 48.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 100,000 | 5 | 44.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 200,000 | 9 | 61.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 200,000 | 5 | 51.2 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 500,000 | 9 | 72.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 500,000 | 5 | 65.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe599-il | 1,000,000 | 9 | 79.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe599-il | 1,000,000 | 5 | 80.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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