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 | ||
(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 |
(mh27-il) MH 27 11.99% | Martin Hepperle MH 27 for F3D Pylon Racing (extended laminar flow) Max thickness 12% at 42.4% chord Max camber 1.4% at 42.4% chord | Remove Airfoil details Airfoil plotter |
(mh24-il) MH 24 9.01% | Martin Hepperle MH 24 for F3D Pylon Racing (extended laminar flow) Max thickness 9% at 37.3% chord Max camber 1.2% at 37.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (mh201-il,mh27-il,mh24-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| mh27-il | 50,000 | 9 | 33.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 50,000 | 5 | 30.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 100,000 | 9 | 49.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 100,000 | 5 | 46.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 200,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 200,000 | 5 | 54.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 500,000 | 9 | 73.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 500,000 | 5 | 54.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh27-il | 1,000,000 | 9 | 73.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh27-il | 1,000,000 | 5 | 61.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 50,000 | 5 | 33 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 9 | 50.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 100,000 | 5 | 47 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 9 | 68.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 200,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 9 | 79.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 500,000 | 5 | 61.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 9 | 74.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh24-il | 1,000,000 | 5 | 70.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||