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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(mh80-il) MH 80 12.72% | Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord Max camber 2.8% at 21.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh80-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh80-il | 50,000 | 9 | 12.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 50,000 | 5 | 22.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 9 | 28.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 9 | 50.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 5 | 58.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 9 | 82.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 5 | 85.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 9 | 109.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 5 | 108.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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