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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(goe238-il) GOE 238 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 238 (HANSA-BRANDENBURG) airfoil Max thickness 9.8% at 29.8% chord Max camber 5.5% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe238-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe238-il | 50,000 | 9 | 9.8 at α=-3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 50,000 | 5 | 24.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 100,000 | 9 | 51.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 100,000 | 5 | 55.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 200,000 | 9 | 80.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 200,000 | 5 | 80.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 500,000 | 9 | 117.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 500,000 | 5 | 110 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe238-il | 1,000,000 | 9 | 143.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe238-il | 1,000,000 | 5 | 130.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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