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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(goe506-il) GOE 506 AIRFOIL | Gottingen 506 airfoil Max thickness 16.5% at 29.3% chord Max camber 4.7% at 39.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe506-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe506-il | 50,000 | 9 | 10.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 100,000 | 9 | 45.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 100,000 | 5 | 40.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 200,000 | 9 | 58 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 200,000 | 5 | 48.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 500,000 | 9 | 64.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 500,000 | 5 | 61.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe506-il | 1,000,000 | 9 | 81.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe506-il | 1,000,000 | 5 | 75.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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