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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(goe495-il) GOE 495 AIRFOIL | Gottingen 495 airfoil Max thickness 6.9% at 30% chord Max camber 5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe495-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe495-il | 50,000 | 9 | 44.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe495-il | 50,000 | 5 | 45.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe495-il | 100,000 | 9 | 69.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe495-il | 100,000 | 5 | 69.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe495-il | 200,000 | 9 | 95.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe495-il | 200,000 | 5 | 93.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe495-il | 500,000 | 9 | 132.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe495-il | 500,000 | 5 | 122.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe495-il | 1,000,000 | 9 | 158.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe495-il | 1,000,000 | 5 | 126.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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