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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(mh60-il) MH 60 10.08% | Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(mh113-il) MH 113 14.62% | Martin Hepperle MH 113 for a propeller for ultralight Max thickness 14.7% at 29.7% chord Max camber 6.4% at 47.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh60-il,mh113-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh60-il | 50,000 | 9 | 27.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh60-il | 50,000 | 5 | 32.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh60-il | 100,000 | 9 | 45 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh60-il | 100,000 | 5 | 46.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh60-il | 200,000 | 9 | 61.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh60-il | 200,000 | 5 | 60 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh60-il | 500,000 | 9 | 82.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh60-il | 500,000 | 5 | 77.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh60-il | 1,000,000 | 9 | 98.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh60-il | 1,000,000 | 5 | 91 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 50,000 | 9 | 6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 50,000 | 5 | 20.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 100,000 | 9 | 50.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 100,000 | 5 | 56 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 200,000 | 9 | 84.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 200,000 | 5 | 83.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 500,000 | 9 | 124.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 500,000 | 5 | 114.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh113-il | 1,000,000 | 9 | 153 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh113-il | 1,000,000 | 5 | 132.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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