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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(mue139-il) MUE 139 | MUE 139 airfoil Max thickness 13.9% at 22.2% chord Max camber 4.7% at 30.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mue139-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mue139-il | 50,000 | 9 | 15.7 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mue139-il | 50,000 | 5 | 27.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mue139-il | 100,000 | 9 | 35.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mue139-il | 100,000 | 5 | 44.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mue139-il | 200,000 | 9 | 58.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mue139-il | 200,000 | 5 | 63.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mue139-il | 500,000 | 9 | 89.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mue139-il | 500,000 | 5 | 90.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mue139-il | 1,000,000 | 9 | 116.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mue139-il | 1,000,000 | 5 | 115.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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