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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(m12-il) NACA M12 AIRFOIL | NACA/Munk M-12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe55-il) GOE 55 AIRFOIL | Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord Max camber 2% at 19.9% chord | Remove Airfoil details Airfoil plotter |
(k3-il) GRUMMAN K-3 AIRFOIL | Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord | Remove Airfoil details Airfoil plotter |
(e396-il) EPPLER 396 AIRFOIL | Eppler E396 human powered aircraft airfoil Max thickness 13.1% at 29.5% chord Max camber 5.4% at 52.1% chord | Remove Airfoil details Airfoil plotter |
(e474-il) E474 (14.09%) | Eppler E474 aerobatic aircraft airfoil Max thickness 14.1% at 21.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m12-il,goe55-il,k3-il,e396-il,e474-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m12-il | 50,000 | 9 | 31.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 50,000 | 5 | 33.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 100,000 | 9 | 49 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 100,000 | 5 | 48.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 200,000 | 5 | 62.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 500,000 | 9 | 86.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 500,000 | 5 | 77.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 9 | 98.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m12-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 50,000 | 9 | 26.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 50,000 | 5 | 32.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 9 | 42.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 100,000 | 5 | 43.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 9 | 54.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 200,000 | 5 | 51.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 9 | 64.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 500,000 | 5 | 64.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 9 | 72.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe55-il | 1,000,000 | 5 | 77.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 50,000 | 9 | 24.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 50,000 | 5 | 23 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 100,000 | 9 | 30.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 100,000 | 5 | 33.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 200,000 | 9 | 49.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 200,000 | 5 | 50.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 500,000 | 9 | 79.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 500,000 | 5 | 65.9 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 9 | 94.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 5 | 70.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 50,000 | 9 | 25.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 50,000 | 5 | 22.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 100,000 | 9 | 54.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 100,000 | 5 | 57.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 200,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 200,000 | 5 | 90.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 500,000 | 9 | 135.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 500,000 | 5 | 128.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 9 | 169.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e396-il | 1,000,000 | 5 | 148 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e474-il | 50,000 | 9 | 18.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e474-il | 50,000 | 5 | 22.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e474-il | 100,000 | 9 | 28.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e474-il | 100,000 | 5 | 35.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e474-il | 200,000 | 9 | 45.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e474-il | 200,000 | 5 | 51.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e474-il | 500,000 | 9 | 73.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e474-il | 500,000 | 5 | 74.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e474-il | 1,000,000 | 9 | 95.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e474-il | 1,000,000 | 5 | 88.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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