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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(mh106-il) MH 106 13.07% | Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh106-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh106-il | 50,000 | 9 | 14.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 50,000 | 5 | 27.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 100,000 | 9 | 42.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 100,000 | 5 | 44.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 200,000 | 9 | 61.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 200,000 | 5 | 60.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 500,000 | 9 | 86.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 500,000 | 5 | 79.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 1,000,000 | 9 | 103.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 1,000,000 | 5 | 87.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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