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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(goe510-il) GOE 510 AIRFOIL | Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe510-il | 50,000 | 9 | 8.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 5 | 29.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 5 | 48.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 9 | 65.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 9 | 106.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 5 | 99.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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