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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(goe570-il) GOE 570 AIRFOIL | Gottingen 570 airfoil Max thickness 33.7% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe570-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe570-il | 50,000 | 9 | 0.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 50,000 | 5 | 2.5 at α=-14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 9 | 7.1 at α=-12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 5 | 6.3 at α=-14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 9 | 7.8 at α=-14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 5 | 10.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 9 | 23.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 5 | 15.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 9 | 20.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 5 | 16.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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