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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(goe405-il) GOE 405 AIRFOIL | Gottingen 405 airfoil Max thickness 11.1% at 30% chord Max camber 6.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe405-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe405-il | 50,000 | 9 | 9.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 50,000 | 5 | 29.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 9 | 54.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 100,000 | 5 | 58.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 9 | 82.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 200,000 | 5 | 80.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 9 | 115.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 500,000 | 5 | 104.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 9 | 137.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe405-il | 1,000,000 | 5 | 126.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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