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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(goe767-il) GOE 767 AIRFOIL | Gottingen 767 airfoil Max thickness 12% at 20% chord Max camber 1.5% at 20% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe767-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe767-il | 50,000 | 9 | 15.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 50,000 | 5 | 23.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 100,000 | 9 | 30.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 100,000 | 5 | 38.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 200,000 | 9 | 49.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 200,000 | 5 | 54.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 500,000 | 9 | 76 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 500,000 | 5 | 74.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe767-il | 1,000,000 | 9 | 93.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe767-il | 1,000,000 | 5 | 91.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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