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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(mh33-il) MH33 | Martin Hepperle MH 33 for F3E and F3B Max thickness 7.3% at 29.3% chord Max camber 1.1% at 43.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh33-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh33-il | 50,000 | 9 | 32.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 50,000 | 5 | 31.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 100,000 | 9 | 46.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 100,000 | 5 | 42.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 200,000 | 9 | 59.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 200,000 | 5 | 51.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 500,000 | 9 | 72.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 500,000 | 5 | 64.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 1,000,000 | 9 | 81.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 1,000,000 | 5 | 74.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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