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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(mh104-il) MH 104 15.28% | Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh104-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh104-il | 50,000 | 9 | 12 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 5 | 21.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 9 | 37.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 5 | 43.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 9 | 62.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 5 | 65 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 9 | 95.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 5 | 92.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 9 | 120.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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