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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(goe592-il) GOE 592 AIRFOIL | Gottingen 592 airfoil Max thickness 14.3% at 29.7% chord Max camber 7.5% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe592-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe592-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 50,000 | 5 | 13.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 9 | 32.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 100,000 | 5 | 45.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 200,000 | 5 | 76.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 500,000 | 5 | 107 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 9 | 142.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe592-il | 1,000,000 | 5 | 124.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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