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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(mh115-il) MH 115 11.06% | Martin Hepperle MH 115 for a propeller for ultralight Max thickness 11.1% at 29.8% chord Max camber 5.5% at 46% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh115-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh115-il | 50,000 | 9 | 28.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 50,000 | 5 | 37.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 100,000 | 9 | 61.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 100,000 | 5 | 64.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 200,000 | 9 | 91.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 200,000 | 5 | 90 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 500,000 | 9 | 130.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 500,000 | 5 | 120.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh115-il | 1,000,000 | 9 | 158.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh115-il | 1,000,000 | 5 | 140.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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