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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(goe500-il) GOE 500 AIRFOIL | Gottingen 500 airfoil Max thickness 10% at 30% chord Max camber 6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe500-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe500-il | 50,000 | 9 | 35.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 50,000 | 5 | 36.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 9 | 64.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 5 | 65.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 9 | 92 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 9 | 131.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 5 | 120.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 9 | 159.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 5 | 120.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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