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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(goe567-il) GOE 567 AIRFOIL | Gottingen 567 airfoil Max thickness 14.8% at 29.5% chord Max camber 5.3% at 49.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe567-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe567-il | 50,000 | 9 | 6.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 50,000 | 5 | 21.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 100,000 | 9 | 49.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 100,000 | 5 | 56 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 200,000 | 9 | 81 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 200,000 | 5 | 79.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 500,000 | 9 | 115.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 500,000 | 5 | 95.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe567-il | 1,000,000 | 9 | 132.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe567-il | 1,000,000 | 5 | 103.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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