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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(goe565-il) GOE 565 AIRFOIL | Gottingen 565 airfoil Max thickness 8.4% at 30% chord Max camber 2.8% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe565-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe565-il | 50,000 | 9 | 37.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 50,000 | 5 | 39.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 100,000 | 9 | 56.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 100,000 | 5 | 55 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 200,000 | 9 | 76.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 200,000 | 5 | 69 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 500,000 | 9 | 98.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 500,000 | 5 | 80.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe565-il | 1,000,000 | 9 | 110.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe565-il | 1,000,000 | 5 | 89.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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