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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(mh42-il) MH 42 8.94% | Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh42-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh42-il | 50,000 | 9 | 32.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 9 | 49.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 5 | 49.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 9 | 67 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 5 | 62.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 9 | 88.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 5 | 78.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 9 | 102 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 5 | 89.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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