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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(goe330-il) GOE 330 (PFALZ 59) AIRFOIL | Gottingen 330 (Pfalz 59) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe330-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe330-il | 50,000 | 9 | 24.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 50,000 | 5 | 38.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 100,000 | 9 | 56.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 100,000 | 5 | 58.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 200,000 | 9 | 78.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 200,000 | 5 | 75.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 500,000 | 9 | 103.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 500,000 | 5 | 101.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe330-il | 1,000,000 | 9 | 128.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe330-il | 1,000,000 | 5 | 121.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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