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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(goe512-il) GOE 512 AIRFOIL | Gottingen 512 airfoil Max thickness 13.9% at 19.9% chord Max camber 5.6% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe512-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe512-il | 50,000 | 9 | 19.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 50,000 | 5 | 31.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 100,000 | 9 | 48.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 100,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 200,000 | 9 | 64.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 200,000 | 5 | 60.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 500,000 | 9 | 83.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 500,000 | 5 | 74.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe512-il | 1,000,000 | 9 | 95.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe512-il | 1,000,000 | 5 | 88.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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