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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(goe316-il) GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL | Gottingen 316 (Hansa-Brandenburg IV.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe316-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe316-il | 50,000 | 9 | 23.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 50,000 | 5 | 34.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 100,000 | 9 | 50.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 100,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 200,000 | 9 | 71.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 200,000 | 5 | 72 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 500,000 | 9 | 100.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 500,000 | 5 | 98.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe316-il | 1,000,000 | 9 | 123.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe316-il | 1,000,000 | 5 | 118.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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