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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(goe498-il) GOE 498 AIRFOIL | Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe498-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe498-il | 50,000 | 9 | 7.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe498-il | 50,000 | 5 | 24.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe498-il | 100,000 | 9 | 49.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe498-il | 100,000 | 5 | 53.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe498-il | 200,000 | 9 | 75.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe498-il | 200,000 | 5 | 73.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe498-il | 500,000 | 9 | 105.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe498-il | 500,000 | 5 | 91.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe498-il | 1,000,000 | 9 | 123.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe498-il | 1,000,000 | 5 | 102.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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