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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(m9-il) NACA M9 AIRFOIL | NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(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 |
(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID) | Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m9-il,mh112-il,marsden-il,marske4-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m9-il | 50,000 | 9 | 15.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 50,000 | 5 | 30.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 100,000 | 9 | 43.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 100,000 | 5 | 49.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 200,000 | 9 | 63.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 200,000 | 5 | 63.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 500,000 | 9 | 80.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 500,000 | 5 | 81.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m9-il | 1,000,000 | 9 | 99.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m9-il | 1,000,000 | 5 | 99.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| marske4-il | 50,000 | 9 | 17 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske4-il | 50,000 | 5 | 22.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske4-il | 100,000 | 9 | 24.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske4-il | 100,000 | 5 | 34.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske4-il | 200,000 | 9 | 39.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske4-il | 200,000 | 5 | 50.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske4-il | 500,000 | 9 | 73.9 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske4-il | 500,000 | 5 | 78.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske4-il | 1,000,000 | 9 | 100.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske4-il | 1,000,000 | 5 | 98.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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