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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(goe332-il) GOE 332 (PFALZ 61) AIRFOIL | Gottingen 332 (Pfalz 61) airfoil Max thickness 11.8% at 29.8% chord Max camber 6.4% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe332-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe332-il | 50,000 | 9 | 10.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 50,000 | 5 | 29.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 100,000 | 9 | 52.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 100,000 | 5 | 59.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 200,000 | 9 | 83.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 200,000 | 5 | 84.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 500,000 | 9 | 120.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 500,000 | 5 | 113.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe332-il | 1,000,000 | 9 | 147.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe332-il | 1,000,000 | 5 | 131.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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