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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(goe738-il) GOE 738 AIRFOIL | Gottingen 738 airfoil Max thickness 15.4% at 30% chord Max camber 2.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe738-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe738-il | 50,000 | 9 | 10.1 at α=-1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe738-il | 50,000 | 5 | 23.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe738-il | 100,000 | 9 | 41.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe738-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe738-il | 200,000 | 9 | 62.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe738-il | 200,000 | 5 | 61.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe738-il | 500,000 | 9 | 87.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe738-il | 500,000 | 5 | 79.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe738-il | 1,000,000 | 9 | 102.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe738-il | 1,000,000 | 5 | 93.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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