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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(goe598-il) GOE 598 AIRFOIL | Gottingen 598 airfoil Max thickness 6.5% at 39.8% chord Max camber 1% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe598-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe598-il | 50,000 | 9 | 31.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe598-il | 50,000 | 5 | 30.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe598-il | 100,000 | 9 | 43.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe598-il | 100,000 | 5 | 40.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe598-il | 200,000 | 9 | 54.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe598-il | 200,000 | 5 | 48.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe598-il | 500,000 | 9 | 66.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe598-il | 500,000 | 5 | 54.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe598-il | 1,000,000 | 9 | 72.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe598-il | 1,000,000 | 5 | 60.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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