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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(goe318-il) GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL | Gottingen 318 (Hansa-Brandenburg VI.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe318-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe318-il | 50,000 | 9 | 20.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 100,000 | 9 | 50.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 100,000 | 5 | 53.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 200,000 | 9 | 69 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 200,000 | 5 | 70 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 500,000 | 9 | 93.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 500,000 | 5 | 92.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 1,000,000 | 9 | 113.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 1,000,000 | 5 | 111 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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