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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(goe79-il) GOE 79 (PFALZ 11) AIRFOIL | Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe79-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe79-il | 50,000 | 9 | 59.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 50,000 | 5 | 42.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 9 | 57.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 100,000 | 5 | 59.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 9 | 75.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 9 | 102.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 500,000 | 5 | 97.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 9 | 120.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe79-il | 1,000,000 | 5 | 103.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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