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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(goe501-il) GOE 501 AIRFOIL | Gottingen 501 airfoil Max thickness 12.8% at 30% chord Max camber 6.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe501-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe501-il | 50,000 | 9 | 9.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 50,000 | 5 | 29.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 100,000 | 9 | 56.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 100,000 | 5 | 60.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 200,000 | 9 | 85.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 200,000 | 5 | 80.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 500,000 | 9 | 113.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 500,000 | 5 | 106.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe501-il | 1,000,000 | 9 | 137.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe501-il | 1,000,000 | 5 | 113.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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