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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(mh22-il) MH 22 7.2% | Martin Hepperle MH 22 for F3D Pylon Racing Max thickness 7.2% at 27% chord Max camber 1.8% at 37% chord | Remove Airfoil details Airfoil plotter |
(mh18-il) MH 18 11.16% | Martin Hepperle MH 18 for F3D Pylon Racing Max thickness 11.1% at 36.8% chord Max camber 2.7% at 42.1% chord | Remove Airfoil details Airfoil plotter |
(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL | NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord | Remove Airfoil details Airfoil plotter |
(mh45-il) MH 45 9.85% | Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh22-il,mh18-il,ms313-il,mh45-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh22-il | 50,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 50,000 | 5 | 35 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 9 | 48.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 100,000 | 5 | 47.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 9 | 63.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 9 | 82.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 500,000 | 5 | 74.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 9 | 92.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh22-il | 1,000,000 | 5 | 81.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 50,000 | 5 | 31.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 100,000 | 5 | 53.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 9 | 77.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 200,000 | 5 | 74.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 9 | 108.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 500,000 | 5 | 96.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 9 | 127.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh18-il | 1,000,000 | 5 | 107.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 50,000 | 9 | 31.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 50,000 | 5 | 29.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 100,000 | 9 | 46.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 100,000 | 5 | 39.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 200,000 | 9 | 55.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 200,000 | 5 | 50.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 500,000 | 9 | 74.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 500,000 | 5 | 69.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 1,000,000 | 9 | 85.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 1,000,000 | 5 | 87.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 9 | 27.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 9 | 44.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 5 | 45.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 9 | 60.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 5 | 58.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 9 | 81.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 5 | 75.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 9 | 95.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 5 | 88.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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