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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(mh120-il) MH 120 11.57% | Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh120-il | 50,000 | 9 | 32.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 50,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 9 | 54.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 5 | 54.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 9 | 76.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 5 | 73.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 9 | 104.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 5 | 95.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 9 | 124.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 5 | 105.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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