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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(goe326-il) GOE 326 (PFALZ 55) AIRFOIL | Gottingen 326 (Pfalz 55) airfoil Max thickness 8.2% at 29.9% chord Max camber 4.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe326-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe326-il | 50,000 | 9 | 32.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe326-il | 50,000 | 5 | 40 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe326-il | 100,000 | 9 | 56.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe326-il | 100,000 | 5 | 59.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe326-il | 200,000 | 9 | 77.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe326-il | 200,000 | 5 | 77.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe326-il | 500,000 | 9 | 104.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe326-il | 500,000 | 5 | 100.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe326-il | 1,000,000 | 9 | 123.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe326-il | 1,000,000 | 5 | 116.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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