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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(goe692-il) GOE 692 AIRFOIL | Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe692-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe692-il | 50,000 | 9 | 7.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 50,000 | 5 | 19 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 9 | 48.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 100,000 | 5 | 49.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 9 | 76.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 200,000 | 5 | 73.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 9 | 109 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 9 | 132.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe692-il | 1,000,000 | 5 | 114.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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