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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(mh46-il) MH 46 9.1% | Martin Hepperle MH 46 for flying wings Max thickness 9.1% at 27.1% chord Max camber 1.4% at 36.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh46-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh46-il | 50,000 | 9 | 30.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh46-il | 50,000 | 5 | 33.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh46-il | 100,000 | 9 | 46 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh46-il | 100,000 | 5 | 46.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh46-il | 200,000 | 9 | 61.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh46-il | 200,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh46-il | 500,000 | 9 | 81.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh46-il | 500,000 | 5 | 74.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh46-il | 1,000,000 | 9 | 94.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh46-il | 1,000,000 | 5 | 85.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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