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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(goe532-il) GOE 532 AIRFOIL | Gottingen 532 airfoil Max thickness 12.5% at 30% chord Max camber 4.8% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe532-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe532-il | 50,000 | 9 | 17.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 50,000 | 5 | 34.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 100,000 | 9 | 53.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 100,000 | 5 | 56 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 200,000 | 9 | 76.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 200,000 | 5 | 73.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 500,000 | 9 | 101.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 500,000 | 5 | 89.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe532-il | 1,000,000 | 9 | 115.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe532-il | 1,000,000 | 5 | 102.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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