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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(m5-il) NACA M5 AIRFOIL | NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(coanda2-il) Coanda 2 | Coanda 2 airfoil Max thickness 6% at 30% chord Max camber 2.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(fxm2-il) WORTMANN FX M2 AIRFOIL | Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord | Remove Airfoil details Airfoil plotter |
(e559-il) EPPLER 559 AIRFOIL | Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m5-il,coanda2-il,fxm2-il,e559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m5-il | 50,000 | 9 | 32.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 100,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 200,000 | 5 | 57.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 500,000 | 9 | 76.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 500,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 9 | 86.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 5 | 76.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 50,000 | 9 | 37.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 50,000 | 5 | 37.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 5 | 48 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 9 | 64.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 5 | 49.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 9 | 62.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 5 | 52.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 9 | 58.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 5 | 58.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 50,000 | 9 | 31.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 50,000 | 5 | 35.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 100,000 | 9 | 45.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 100,000 | 5 | 50.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 200,000 | 9 | 65.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 200,000 | 5 | 68.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 500,000 | 9 | 94.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 500,000 | 5 | 86.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 1,000,000 | 9 | 103.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 1,000,000 | 5 | 100.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 50,000 | 9 | 8.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 50,000 | 5 | 30.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 100,000 | 9 | 43.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 100,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 200,000 | 9 | 70.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 200,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 500,000 | 5 | 101.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 9 | 130.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 5 | 123.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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