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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(goe364-il) GOE 364 AIRFOIL | Gottingen 364 airfoil Max thickness 10.8% at 30% chord Max camber 6.5% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe364-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe364-il | 50,000 | 9 | 13.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 100,000 | 9 | 52.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 100,000 | 5 | 57 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 200,000 | 9 | 76.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 500,000 | 9 | 107.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 500,000 | 5 | 104 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 1,000,000 | 9 | 133.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 1,000,000 | 5 | 124.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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