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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(goe447-il) GOE 447 AIRFOIL | Gottingen 447 airfoil Max thickness 12.7% at 29.7% chord Max camber 8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe447-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe447-il | 50,000 | 9 | 6.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 50,000 | 5 | 16 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 100,000 | 9 | 40 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 100,000 | 5 | 49.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 200,000 | 9 | 84 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 200,000 | 5 | 84.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 500,000 | 9 | 129.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 500,000 | 5 | 116.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe447-il | 1,000,000 | 9 | 161.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe447-il | 1,000,000 | 5 | 126.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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