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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(goe446-il) GOE 446 AIRFOIL | Gottingen 446 airfoil Max thickness 12.9% at 29.7% chord Max camber 6.3% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe446-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe446-il | 50,000 | 9 | 7.6 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe446-il | 50,000 | 5 | 21.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe446-il | 100,000 | 9 | 50.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe446-il | 100,000 | 5 | 56.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe446-il | 200,000 | 9 | 83.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe446-il | 200,000 | 5 | 83.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe446-il | 500,000 | 9 | 122 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe446-il | 500,000 | 5 | 111.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe446-il | 1,000,000 | 9 | 148.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe446-il | 1,000,000 | 5 | 130.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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