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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(goe385-il) GOE 385 AIRFOIL | Gottingen 385 airfoil Max thickness 9.9% at 29.9% chord Max camber 4.1% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe385-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe385-il | 50,000 | 9 | 29.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 50,000 | 5 | 37.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 100,000 | 9 | 51.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 100,000 | 5 | 56.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 200,000 | 9 | 73 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 200,000 | 5 | 72.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 500,000 | 9 | 97.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 500,000 | 5 | 93.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe385-il | 1,000,000 | 9 | 115.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe385-il | 1,000,000 | 5 | 108.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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