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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(goe344-il) GOE 344 (PFALZ 71) AIRFOIL | Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe344-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe344-il | 50,000 | 9 | 32.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 50,000 | 5 | 34.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 100,000 | 9 | 45.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 100,000 | 5 | 47.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 200,000 | 9 | 60.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 200,000 | 5 | 60.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 500,000 | 9 | 80.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 500,000 | 5 | 77.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe344-il | 1,000,000 | 9 | 95.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe344-il | 1,000,000 | 5 | 89 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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