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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(goe744-il) GOE 744 AIRFOIL | Gottingen 744 airfoil Max thickness 14.5% at 20% chord Max camber 7% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe744-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe744-il | 50,000 | 9 | 3.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 50,000 | 5 | 7.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 100,000 | 9 | 5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 200,000 | 9 | 56.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 200,000 | 5 | 64.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 500,000 | 9 | 98.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 500,000 | 5 | 97.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 1,000,000 | 9 | 128.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 1,000,000 | 5 | 114.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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