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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(goe429-il) GOE 429 AIRFOIL | Gottingen 429 airfoil Max thickness 11.4% at 30% chord Max camber 0.2% at 10% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe429-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe429-il | 50,000 | 9 | 23.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 50,000 | 5 | 26.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 100,000 | 9 | 35.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 100,000 | 5 | 37.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 200,000 | 9 | 47.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 200,000 | 5 | 45.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 500,000 | 9 | 57.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 500,000 | 5 | 58.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe429-il | 1,000,000 | 9 | 67.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe429-il | 1,000,000 | 5 | 72.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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