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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(goe445-il) GOE 445 AIRFOIL | Gottingen 445 airfoil Max thickness 6.4% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe445-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe445-il | 50,000 | 9 | 18.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe445-il | 50,000 | 5 | 19.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe445-il | 100,000 | 9 | 24.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe445-il | 100,000 | 5 | 30.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe445-il | 200,000 | 9 | 42.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe445-il | 200,000 | 5 | 39 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe445-il | 500,000 | 9 | 49.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe445-il | 500,000 | 5 | 38 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe445-il | 1,000,000 | 9 | 46.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe445-il | 1,000,000 | 5 | 42.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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