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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(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 |
(mh24-il) MH 24 9.01% | Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh81-il,mh24-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| mh24-il | 50,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 5 | 33 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 9 | 50.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 9 | 68.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 9 | 74.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 5 | 70.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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