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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(mh38-il) MH 38 9.68% | Martin Hepperle MH 38 for Endurance Model Max thickness 9.7% at 31.6% chord Max camber 3.9% at 45.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh38-il | 50,000 | 9 | 37.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 50,000 | 5 | 37.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 100,000 | 9 | 61.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 100,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 200,000 | 9 | 86.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 200,000 | 5 | 85.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 500,000 | 9 | 122.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 500,000 | 5 | 114.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh38-il | 1,000,000 | 9 | 149.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh38-il | 1,000,000 | 5 | 133.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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