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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(goe418-il) GOE 418 AIRFOIL | Gottingen 418 airfoil Max thickness 12.7% at 20% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe432-il) GOE 432 AIRFOIL | Gottingen 432 airfoil Max thickness 7.7% at 20% chord Max camber 4.3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe418-il,goe432-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe418-il | 50,000 | 9 | 12.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe418-il | 50,000 | 5 | 32.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe418-il | 100,000 | 9 | 52.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe418-il | 100,000 | 5 | 54 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe418-il | 200,000 | 9 | 75.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe418-il | 200,000 | 5 | 71.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe418-il | 500,000 | 9 | 101.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe418-il | 500,000 | 5 | 90.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe418-il | 1,000,000 | 9 | 117.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe418-il | 1,000,000 | 5 | 92.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 50,000 | 9 | 35.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 50,000 | 5 | 40.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 100,000 | 9 | 53.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 100,000 | 5 | 56.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 200,000 | 9 | 72.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 200,000 | 5 | 72 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 500,000 | 9 | 94.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 500,000 | 5 | 88.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe432-il | 1,000,000 | 9 | 108 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe432-il | 1,000,000 | 5 | 107.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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