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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(goe396-il) GOE 396 AIRFOIL | Gottingen 396 airfoil Max thickness 4.7% at 30% chord Max camber 5.8% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe396-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe396-il | 50,000 | 9 | 44.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe396-il | 50,000 | 5 | 44.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe396-il | 100,000 | 9 | 67 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe396-il | 100,000 | 5 | 66.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe396-il | 200,000 | 5 | 89.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe396-il | 200,000 | 0 | 92.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe396-il | 500,000 | 9 | 121.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe396-il | 500,000 | 5 | 111.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe396-il | 1,000,000 | 9 | 141.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe396-il | 1,000,000 | 5 | 99.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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