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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(goe629-il) GOE 629 AIRFOIL | Gottingen 629 airfoil Max thickness 13.6% at 29.4% chord Max camber 2.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe629-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe629-il | 50,000 | 9 | 29.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe629-il | 50,000 | 5 | 32.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe629-il | 100,000 | 9 | 50.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe629-il | 100,000 | 5 | 50.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe629-il | 200,000 | 9 | 70 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe629-il | 200,000 | 5 | 66.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe629-il | 500,000 | 9 | 94.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe629-il | 500,000 | 5 | 81.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe629-il | 1,000,000 | 9 | 107.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe629-il | 1,000,000 | 5 | 92.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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