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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(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 |
(mh81-il) MH 81 13% | Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(mh70-il) MH 70 11.08% | Martin Hepperle MH 70 for fying wing (full size) Max thickness 11.1% at 29.4% chord Max camber 3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(mh94-il) MH 94 16.03% | Martin Hepperle MH 94 parafoil Max thickness 16% at 34.1% chord Max camber 1.3% at 74.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mrc-20-il,mh81-il,mh70-il,mh94-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| mh81-il | 50,000 | 9 | 11.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 5 | 23 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 9 | 52 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 5 | 60.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 9 | 85.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 5 | 88.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 9 | 112.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 5 | 111.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 50,000 | 9 | 27.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 50,000 | 5 | 35.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 9 | 50.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 100,000 | 5 | 52.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 200,000 | 5 | 67.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 9 | 95 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 500,000 | 5 | 87.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 9 | 112.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh70-il | 1,000,000 | 5 | 103.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh94-il | 50,000 | 9 | 29.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh94-il | 50,000 | 5 | 27.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh94-il | 100,000 | 9 | 40.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh94-il | 100,000 | 5 | 36.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh94-il | 200,000 | 9 | 46.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh94-il | 200,000 | 5 | 45.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh94-il | 500,000 | 9 | 62.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh94-il | 500,000 | 5 | 61.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh94-il | 1,000,000 | 9 | 76.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh94-il | 1,000,000 | 5 | 75.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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