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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(goe534-il) GOE 534 AIRFOIL | Gottingen 534 airfoil Max thickness 14.1% at 19.6% chord Max camber 5.2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe534-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe534-il | 50,000 | 9 | 20 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 50,000 | 5 | 32.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 100,000 | 9 | 44 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 100,000 | 5 | 50.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 200,000 | 9 | 65.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 200,000 | 5 | 67.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 500,000 | 9 | 93.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe534-il | 1,000,000 | 9 | 114.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe534-il | 1,000,000 | 5 | 110.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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