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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(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 |
(mh200-il) MH 200 12.97% | Martin Hepperle MH 200 for a canard airplane (main wing) Max thickness 13% at 39.5% chord Max camber 2.1% at 49.8% chord | Remove Airfoil details Airfoil plotter |
(mh104-il) MH 104 15.28% | Martin Hepperle MH 104 for stall controlled wind turbines Max thickness 15.2% at 26.4% chord Max camber 1.9% at 31.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh122-il,mh200-il,mh104-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| mh200-il | 50,000 | 9 | 33.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 9 | 53.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 100,000 | 5 | 51 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 9 | 76.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 200,000 | 5 | 66.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 9 | 98.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 500,000 | 5 | 85.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 9 | 117 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh200-il | 1,000,000 | 5 | 93.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 9 | 12 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 50,000 | 5 | 21.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 9 | 37.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 100,000 | 5 | 43.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 9 | 62.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 200,000 | 5 | 65 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 9 | 95.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 500,000 | 5 | 92.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 9 | 120.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh104-il | 1,000,000 | 5 | 106.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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