Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(mh64-il) MH 64 8.59% | Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (mh64-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh64-il | 50,000 | 9 | 29.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 50,000 | 5 | 33.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 100,000 | 9 | 44.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 100,000 | 5 | 45.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 200,000 | 9 | 59.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 200,000 | 5 | 57 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 500,000 | 9 | 78 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 500,000 | 5 | 72.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh64-il | 1,000,000 | 9 | 90.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh64-il | 1,000,000 | 5 | 84 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||