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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(n2h15-il) NACA 2-H-15 AIRFOIL | NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(mh81-il) MH 81 13% | Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord | Remove Airfoil details Airfoil plotter |
(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 |
(miley-il) MILEY M06-13-128 | Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord | Remove Airfoil details Airfoil plotter |
(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 (n2h15-il,mh81-il,mh64-il,miley-il,mh38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n2h15-il | 50,000 | 9 | 18.1 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 5 | 13.4 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 9 | 20 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 5 | 20.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 9 | 34.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 5 | 38.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 9 | 110.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 5 | 107.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 9 | 145.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 5 | 122.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 9 | 11.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 50,000 | 5 | 23 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 100,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 9 | 52 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 200,000 | 5 | 60.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 9 | 85.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 500,000 | 5 | 88.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 9 | 112.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh81-il | 1,000,000 | 5 | 111.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| miley-il | 50,000 | 9 | 5.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 50,000 | 5 | 11 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 100,000 | 9 | 23.5 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 100,000 | 5 | 23.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 200,000 | 9 | 61.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 200,000 | 5 | 62.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 500,000 | 9 | 122.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 500,000 | 5 | 121.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 9 | 168 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 5 | 157.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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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