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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(goe559-il) GOE 559 AIRFOIL | Gottingen 559 airfoil Max thickness 11.2% at 30% chord Max camber 3.4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe559-il | 50,000 | 9 | 30.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 50,000 | 5 | 28.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 9 | 40.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 100,000 | 5 | 38.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 9 | 50.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 200,000 | 5 | 50 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 9 | 66.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 500,000 | 5 | 64.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 9 | 76.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe559-il | 1,000,000 | 5 | 74.2 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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