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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(fx72150a-il) WORTMANN FX 72-MS-150A AIRFOIL | Wortmann FX 72-MS-150A airfoil Max thickness 15% at 37.1% chord Max camber 8.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(mh201-il) MH 201 13.08% | Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx72150a-il,mh201-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx72150a-il | 50,000 | 9 | 6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 50,000 | 5 | 10.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 9 | 13.2 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 100,000 | 5 | 40.5 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 9 | 58.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 200,000 | 5 | 78.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 9 | 123.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 500,000 | 5 | 121.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 9 | 160.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx72150a-il | 1,000,000 | 5 | 154 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 50,000 | 9 | 33.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 50,000 | 5 | 34.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 100,000 | 9 | 55 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 100,000 | 5 | 52.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 200,000 | 9 | 73.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 200,000 | 5 | 67 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 500,000 | 9 | 95.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 500,000 | 5 | 85.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh201-il | 1,000,000 | 9 | 113.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh201-il | 1,000,000 | 5 | 95.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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