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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(mh116-il) MH 116 9.84% | Martin Hepperle MH 116 for a propeller for ultralight Max thickness 9.9% at 32.4% chord Max camber 4.1% at 46.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh116-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh116-il | 50,000 | 9 | 39 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 50,000 | 5 | 39.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 100,000 | 9 | 63 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 100,000 | 5 | 63 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 200,000 | 9 | 89.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 200,000 | 5 | 86.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 500,000 | 9 | 125.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh116-il | 1,000,000 | 9 | 150.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh116-il | 1,000,000 | 5 | 131 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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