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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(goe511-il) GOE 511 AIRFOIL | Gottingen 511 airfoil Max thickness 16.6% at 19.9% chord Max camber 8% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe511-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe511-il | 50,000 | 9 | 3.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 50,000 | 5 | 25.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 100,000 | 9 | 41.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 100,000 | 5 | 41.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 200,000 | 9 | 57.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 200,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 500,000 | 9 | 71.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 500,000 | 5 | 67 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe511-il | 1,000,000 | 9 | 87.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe511-il | 1,000,000 | 5 | 80.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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