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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(mh80-il) MH 80 12.72% | Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord Max camber 2.8% at 21.7% chord | Remove Airfoil details Airfoil plotter |
(n14-il) N-14 | N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord | Remove Airfoil details Airfoil plotter |
(mh84-il) MH 84 13.69% | Martin Hepperle MH 84 for flying wings (hang glider) Max thickness 13.7% at 21.5% chord Max camber 4.1% at 36.6% 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 |
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Polars for (mh80-il,n14-il,mh84-il,marsden-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh80-il | 50,000 | 9 | 12.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 50,000 | 5 | 22.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 9 | 28.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 9 | 50.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 200,000 | 5 | 58.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 9 | 82.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 500,000 | 5 | 85.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 9 | 109.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh80-il | 1,000,000 | 5 | 108.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 50,000 | 9 | 29.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 50,000 | 5 | 27.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 100,000 | 9 | 40.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 100,000 | 5 | 36.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 200,000 | 9 | 48.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 200,000 | 5 | 44.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 500,000 | 9 | 56.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 500,000 | 5 | 58.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n14-il | 1,000,000 | 9 | 71.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n14-il | 1,000,000 | 5 | 73.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 50,000 | 9 | 15.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 50,000 | 5 | 30.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 9 | 40.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 9 | 62.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 200,000 | 5 | 66.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 9 | 92.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 500,000 | 5 | 92 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 9 | 116.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh84-il | 1,000,000 | 5 | 113 at α=7.5° | 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 | |
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