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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(mh110-il) MH 110 10.01% | Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh110-il | 50,000 | 9 | 16.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 50,000 | 5 | 25.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 9 | 39 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 5 | 41 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 9 | 56.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 5 | 56 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 9 | 78.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 5 | 75.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 9 | 94.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 5 | 88.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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