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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(mh114-il) MH 114 13.02% | Martin Hepperle MH 114 for a propeller for ultralight Max thickness 13% at 28.1% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh114-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh114-il | 50,000 | 9 | 9.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 9 | 56.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 100,000 | 5 | 60.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 9 | 89.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 200,000 | 5 | 88.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 500,000 | 5 | 121 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 9 | 161 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh114-il | 1,000,000 | 5 | 140.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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