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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(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL | Gottingen 235 (SCHATTE-LANZ) airfoil Max thickness 6.5% at 19.9% chord Max camber 3.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe235-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe235-il | 50,000 | 9 | 36.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 5 | 37.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 9 | 52.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 5 | 48 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 9 | 60.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 5 | 57.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 9 | 73.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 5 | 68.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 9 | 80.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 5 | 81.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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