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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(goe482-il) GOE 482 AIRFOIL | Gottingen 482 airfoil Max thickness 16.5% at 29.6% chord Max camber 8.8% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe482-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe482-il | 50,000 | 9 | 4.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 50,000 | 5 | 17.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 100,000 | 9 | 35.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 100,000 | 5 | 51 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 200,000 | 9 | 71.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 200,000 | 5 | 73.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 500,000 | 9 | 107.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 500,000 | 5 | 100.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 1,000,000 | 9 | 137.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 1,000,000 | 5 | 121.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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