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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(goe723-il) GOE 723 AIRFOIL | Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe723-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe723-il | 50,000 | 9 | 32 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 50,000 | 5 | 33.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 9 | 58.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 100,000 | 5 | 58.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 9 | 82.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 200,000 | 5 | 79.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 9 | 114 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 500,000 | 5 | 103.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 9 | 136.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe723-il | 1,000,000 | 5 | 112 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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