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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(goe563-il) GOE 563 AIRFOIL | Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe563-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe563-il | 50,000 | 9 | 35.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 50,000 | 5 | 36.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 100,000 | 9 | 54.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 100,000 | 5 | 51 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 200,000 | 9 | 73.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 200,000 | 5 | 64.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 500,000 | 9 | 95.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 500,000 | 5 | 76.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 1,000,000 | 9 | 105.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 1,000,000 | 5 | 86.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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