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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(ma409sm-il) MA409 (smoothed) | Michael Achterberg MA409 F1C class free flight airfoil (smoothed) Max thickness 6.7% at 23.8% chord Max camber 3.3% at 49.3% 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 (ma409sm-il,mh45-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ma409sm-il | 50,000 | 9 | 43.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 50,000 | 5 | 43.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 100,000 | 9 | 64.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 100,000 | 5 | 62.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 200,000 | 9 | 88.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 200,000 | 5 | 81.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 500,000 | 9 | 121.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 500,000 | 5 | 100.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409sm-il | 1,000,000 | 9 | 140.9 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409sm-il | 1,000,000 | 5 | 112.2 at α=2.5° | 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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