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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(goe399-il) GOE 399 AIRFOIL | Gottingen 399 airfoil Max thickness 6.9% at 29.9% chord Max camber 4.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe399-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe399-il | 50,000 | 9 | 40.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 50,000 | 5 | 41.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 100,000 | 9 | 59.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 100,000 | 5 | 60.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 200,000 | 9 | 79.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 200,000 | 5 | 76.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 500,000 | 9 | 104.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 500,000 | 5 | 98.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe399-il | 1,000,000 | 9 | 124.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe399-il | 1,000,000 | 5 | 112.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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