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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(goe497-il) GOE 497 AIRFOIL | Gottingen 497 airfoil Max thickness 12.7% at 30% chord Max camber 5.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe497-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe497-il | 50,000 | 9 | 28.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe497-il | 50,000 | 5 | 34.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe497-il | 100,000 | 9 | 58.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe497-il | 100,000 | 5 | 60.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe497-il | 200,000 | 9 | 85 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe497-il | 200,000 | 5 | 82 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe497-il | 500,000 | 9 | 118 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe497-il | 500,000 | 5 | 105.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe497-il | 1,000,000 | 9 | 135.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe497-il | 1,000,000 | 5 | 114.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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