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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(goe256-il) GOE 256 (JUNKERS E) AIRFOIL | Gottingen 256 (JUNKERS E) airfoil Max thickness 16% at 29.6% chord Max camber 4.7% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe600-il) GOE 600 AIRFOIL | Gottingen 600 airfoil Max thickness 13.1% at 29.4% chord Max camber 1.9% at 49.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe256-il,goe600-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe256-il | 50,000 | 9 | 6.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe256-il | 50,000 | 5 | 22.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe256-il | 100,000 | 9 | 45.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe256-il | 100,000 | 5 | 48.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe256-il | 200,000 | 9 | 69.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe256-il | 200,000 | 5 | 64.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe256-il | 500,000 | 9 | 92.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe256-il | 500,000 | 5 | 86.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe256-il | 1,000,000 | 9 | 112.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe256-il | 1,000,000 | 5 | 103.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 9 | 32.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 50,000 | 5 | 33.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 100,000 | 5 | 49.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 9 | 69.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 200,000 | 5 | 62.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 9 | 91.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 500,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 9 | 99.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe600-il | 1,000,000 | 5 | 86 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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