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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(mh91-il) MH 91 14.98% | Martin Hepperle MH 91 parafoil Max thickness 15% at 27.3% chord Max camber 1.4% at 18.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh91-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh91-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 50,000 | 5 | 25.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 9 | 34.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 100,000 | 5 | 40.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 200,000 | 5 | 55.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 9 | 78.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 500,000 | 5 | 75.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 9 | 96.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh91-il | 1,000,000 | 5 | 91.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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