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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(n9-il) N-9 | N-9 airfoil Max thickness 8.5% at 30% chord Max camber 2.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(nacam3-il) NACA M3 | NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(mh83-il) MH 83 13.29% | Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord | Remove Airfoil details Airfoil plotter |
(naca64210-il) NACA 64-210 | NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n9-il,nacam3-il,mh83-il,naca64210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n9-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 50,000 | 5 | 38.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 100,000 | 9 | 53.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 100,000 | 5 | 51.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 200,000 | 9 | 68.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 200,000 | 5 | 63.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 500,000 | 9 | 84 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 500,000 | 5 | 78.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n9-il | 1,000,000 | 9 | 96.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n9-il | 1,000,000 | 5 | 92.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 9 | 27.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 5 | 26.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 9 | 37.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 5 | 34.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 5 | 42.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 9 | 54.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 5 | 69.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 50,000 | 9 | 12.8 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 50,000 | 5 | 26.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 100,000 | 9 | 34.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 100,000 | 5 | 46.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 200,000 | 9 | 59.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 200,000 | 5 | 67.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 500,000 | 9 | 94.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 500,000 | 5 | 97.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh83-il | 1,000,000 | 9 | 123.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh83-il | 1,000,000 | 5 | 123.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 9 | 30.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 50,000 | 5 | 32.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 9 | 61.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 200,000 | 5 | 54 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 9 | 76.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 500,000 | 5 | 63.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 9 | 85.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64210-il | 1,000,000 | 5 | 72.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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