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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(goe456-il) GOE 456 AIRFOIL | Gottingen 456 airfoil Max thickness 7.2% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe456-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe456-il | 50,000 | 9 | 42.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 100,000 | 9 | 65.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 100,000 | 5 | 64.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 200,000 | 9 | 87.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 200,000 | 5 | 86.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 500,000 | 9 | 117.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 500,000 | 5 | 115.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 1,000,000 | 9 | 140.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 1,000,000 | 5 | 134.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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