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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(miley-il) MILEY M06-13-128 | Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (miley-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| miley-il | 50,000 | 9 | 5.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 50,000 | 5 | 11 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 100,000 | 9 | 23.5 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 100,000 | 5 | 23.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 200,000 | 9 | 61.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 200,000 | 5 | 62.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 500,000 | 9 | 122.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 500,000 | 5 | 121.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 9 | 168 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 5 | 157.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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