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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(goe369-il) GOE 369 AIRFOIL | Gottingen 369 airfoil Max thickness 5.9% at 30% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe369-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe369-il | 50,000 | 9 | 37.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 50,000 | 5 | 43.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 100,000 | 9 | 59.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 100,000 | 5 | 63.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 200,000 | 9 | 80.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 200,000 | 5 | 83 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 500,000 | 9 | 105.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 500,000 | 5 | 94.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe369-il | 1,000,000 | 9 | 121.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe369-il | 1,000,000 | 5 | 112.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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