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 | ||
(naca651212-il) NACA 65(1)-212 | NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(mh150-il) MH 150 23.89% | Martin Hepperle MH 150 for marine ruddershaft for torque reduction (schottel units) Max thickness 23.9% at 27.2% chord Max camber 4.5% at 53.8% chord | Remove Airfoil details Airfoil plotter |
(mh108-il) MH 108 11.98% | Martin Hepperle MH 108 for stall controlled wind turbines Max thickness 11.9% at 22.8% chord Max camber 1% at 22.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca651212-il,mh150-il,mh108-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca651212-il | 50,000 | 9 | 26.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 50,000 | 5 | 28.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 100,000 | 9 | 46.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 100,000 | 5 | 42.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 200,000 | 9 | 55.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 200,000 | 5 | 52.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 500,000 | 9 | 76.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 500,000 | 5 | 66.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212-il | 1,000,000 | 9 | 87.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212-il | 1,000,000 | 5 | 70.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 50,000 | 9 | 3.9 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 50,000 | 5 | 7.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 100,000 | 9 | 14.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 100,000 | 5 | 38.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 200,000 | 9 | 56.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 200,000 | 5 | 61.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 500,000 | 9 | 90.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 500,000 | 5 | 88.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh150-il | 1,000,000 | 9 | 117.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh150-il | 1,000,000 | 5 | 112.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 50,000 | 9 | 16.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 50,000 | 5 | 25.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 100,000 | 9 | 36.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 100,000 | 5 | 42.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 200,000 | 9 | 56.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 200,000 | 5 | 58.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 500,000 | 9 | 82.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 500,000 | 5 | 79.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh108-il | 1,000,000 | 9 | 102 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh108-il | 1,000,000 | 5 | 93.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||