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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(goe652-il) GOE 652 AIRFOIL | Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe652-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe652-il | 50,000 | 9 | 5.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 50,000 | 5 | 21.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 9 | 49.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 5 | 53.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 9 | 77.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 5 | 78 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 9 | 112.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 5 | 102.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 9 | 135.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 5 | 115.7 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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