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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(goe320-il) GOE 320 (HANSA-BRANDENBURG II.1) AIRFOIL | Gottingen 320 (Hansa-Brandenburg II.1) airfoil Max thickness 12.3% at 29.8% chord Max camber 6.2% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe320-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe320-il | 50,000 | 9 | 29.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe320-il | 50,000 | 5 | 33.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe320-il | 100,000 | 9 | 52.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe320-il | 100,000 | 5 | 48.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe320-il | 200,000 | 9 | 66.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe320-il | 200,000 | 5 | 63.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe320-il | 500,000 | 9 | 89.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe320-il | 500,000 | 5 | 85 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe320-il | 1,000,000 | 9 | 109.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe320-il | 1,000,000 | 5 | 98.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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