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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(mh92-il) MH 92 15.49% | Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh92-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh92-il | 50,000 | 9 | 15.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 50,000 | 5 | 24.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 5 | 40 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 5 | 54.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 9 | 76.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 5 | 73.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 9 | 94.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 5 | 90.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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