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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(goe430-il) GOE 430 AIRFOIL | Gottingen 430 airfoil Max thickness 13.4% at 29.5% chord Max camber 4.8% at 49.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe430-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe430-il | 50,000 | 9 | 30.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 50,000 | 5 | 36.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 100,000 | 9 | 59.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 100,000 | 5 | 60.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 200,000 | 9 | 83.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 200,000 | 5 | 79.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 500,000 | 9 | 111.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 500,000 | 5 | 96.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe430-il | 1,000,000 | 9 | 125.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe430-il | 1,000,000 | 5 | 104.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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