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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(goe564-il) GOE 564 AIRFOIL | Gottingen 564 airfoil Max thickness 8.2% at 30% chord Max camber 2.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe564-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe564-il | 50,000 | 9 | 37.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 50,000 | 5 | 37.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 100,000 | 9 | 56 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 100,000 | 5 | 52.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 200,000 | 9 | 75.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 200,000 | 5 | 65.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 500,000 | 9 | 95.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 500,000 | 5 | 77.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe564-il | 1,000,000 | 9 | 103.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe564-il | 1,000,000 | 5 | 89.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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