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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(goe477-il) GOE 477 AIRFOIL | Gottingen 477 airfoil Max thickness 10.1% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe477-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe477-il | 50,000 | 9 | 34.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 50,000 | 5 | 36.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 9 | 56.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 100,000 | 5 | 54.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 9 | 80.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 200,000 | 5 | 75 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 9 | 111.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 500,000 | 5 | 87.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 9 | 121.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe477-il | 1,000,000 | 5 | 104.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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