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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(goe490-il) GOE 490 AIRFOIL | Gottingen 490 airfoil Max thickness 8.8% at 19.9% chord Max camber 3.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe490-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe490-il | 50,000 | 9 | 33.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe490-il | 50,000 | 5 | 38.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe490-il | 100,000 | 9 | 54.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe490-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe490-il | 200,000 | 9 | 72.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe490-il | 200,000 | 5 | 70.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe490-il | 500,000 | 9 | 96.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe490-il | 500,000 | 5 | 89.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe490-il | 1,000,000 | 9 | 114.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe490-il | 1,000,000 | 5 | 98.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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