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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(mh102-il) MH 102 16.99% | Martin Hepperle MH 102 for stall controlled wind turbines (root) Max thickness 17% at 27.7% chord Max camber 2.8% at 37.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh102-il | 50,000 | 9 | 5.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 50,000 | 5 | 23.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 100,000 | 9 | 37.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 100,000 | 5 | 45.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 200,000 | 9 | 63.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 200,000 | 5 | 65.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 500,000 | 9 | 94.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 500,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh102-il | 1,000,000 | 9 | 118.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh102-il | 1,000,000 | 5 | 110.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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