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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(goe479-il) GOE 479 AIRFOIL | Gottingen 479 airfoil Max thickness 11.6% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe479-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe479-il | 50,000 | 9 | 31.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 50,000 | 5 | 35.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 100,000 | 9 | 53.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 100,000 | 5 | 55.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 200,000 | 9 | 75.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 200,000 | 5 | 72.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 500,000 | 9 | 101.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 500,000 | 5 | 94.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe479-il | 1,000,000 | 9 | 121.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe479-il | 1,000,000 | 5 | 110.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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