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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(mh106-il) MH 106 13.07% | Martin Hepperle MH 106 for stall controlled wind turbines Max thickness 13.1% at 27.4% chord Max camber 0.9% at 27.4% chord | Remove Airfoil details Airfoil plotter |
(mh122-il) MH 122 9.32% | Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord | Remove Airfoil details Airfoil plotter |
(mh81-il) MH 81 13% | Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(mh42-il) MH 42 8.94% | Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh106-il,mh122-il,mh81-il,mh42-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh106-il | 50,000 | 9 | 14.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 50,000 | 5 | 27.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 100,000 | 9 | 42.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 100,000 | 5 | 44.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 200,000 | 9 | 61.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 200,000 | 5 | 60.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 500,000 | 9 | 86.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 500,000 | 5 | 79.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh106-il | 1,000,000 | 9 | 103.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh106-il | 1,000,000 | 5 | 87.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 9 | 38 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 50,000 | 5 | 38 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 9 | 61.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 100,000 | 5 | 58.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 9 | 90.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 200,000 | 5 | 87.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 9 | 137.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 500,000 | 5 | 114.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 9 | 161.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh122-il | 1,000,000 | 5 | 125.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 9 | 11.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 5 | 23 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 9 | 52 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 5 | 60.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 9 | 85.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 5 | 88.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 9 | 112.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 5 | 111.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 50,000 | 9 | 32.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 9 | 49.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 100,000 | 5 | 49.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 9 | 67 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 200,000 | 5 | 62.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 9 | 88.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 500,000 | 5 | 78.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 9 | 102 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh42-il | 1,000,000 | 5 | 89.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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