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 |
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Polars for (mh122-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 | |
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