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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(mh112-il) MH 112 Airfoil | Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord Max camber 6.7% at 48.5% chord | Remove Airfoil details Airfoil plotter |
(marsden-il) Marsden | Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord | Remove Airfoil details Airfoil plotter |
(mrc-20-il) MRC-20 | Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh112-il,marsden-il,mrc-20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh112-il | 50,000 | 9 | 5.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 50,000 | 5 | 14.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 9 | 37.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 5 | 48.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 5 | 79.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 9 | 120 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 9 | 147.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 5 | 126.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 50,000 | 9 | 3 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 50,000 | 5 | 3.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 9 | 3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 5 | 4.7 at α=-10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 9 | 5.1 at α=-8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 5 | 17 at α=-2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 9 | 28.7 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 5 | 59.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 9 | 70.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 5 | 98 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 9 | 23.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 5 | 29.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 9 | 50.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 5 | 50.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 9 | 73.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 5 | 68.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 9 | 99.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 5 | 86.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 9 | 114.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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