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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(goe323-il) GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL | Gottingen 323 (Hansa-Brandenburg V.1) airfoil Max thickness 11.1% at 29.8% chord Max camber 5.2% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe323-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe323-il | 50,000 | 9 | 11.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe323-il | 50,000 | 5 | 29.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe323-il | 100,000 | 9 | 48.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe323-il | 100,000 | 5 | 54.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe323-il | 200,000 | 9 | 75.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe323-il | 200,000 | 5 | 74.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe323-il | 500,000 | 9 | 106.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe323-il | 500,000 | 5 | 96.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe323-il | 1,000,000 | 9 | 125.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe323-il | 1,000,000 | 5 | 114.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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