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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(m16-il) NACA M16 AIRFOIL | NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(e210-il) E210 (13.64%) | Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord | Remove Airfoil details Airfoil plotter |
(goe331-il) GOE 331 (PFALZ 60) AIRFOIL | Gottingen 331 (Pfalz 60) airfoil Max thickness 10.6% at 29.9% chord Max camber 6.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e344-il) EPPLER 344 AIRFOIL | Eppler E344 flying wing airfoil Max thickness 14.7% at 29.9% chord Max camber 4.3% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m16-il,e210-il,goe331-il,e344-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m16-il | 50,000 | 9 | 39 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 100,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 100,000 | 5 | 53.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 200,000 | 9 | 70.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 200,000 | 5 | 68.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 500,000 | 9 | 92.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 500,000 | 5 | 88.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 9 | 109.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m16-il | 1,000,000 | 5 | 102.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 50,000 | 9 | 9.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 50,000 | 5 | 30.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 100,000 | 9 | 52.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 100,000 | 5 | 57.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 200,000 | 9 | 78.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 200,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 500,000 | 9 | 113 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 500,000 | 5 | 109 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 9 | 140.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e210-il | 1,000,000 | 5 | 129.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 9 | 22.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 9 | 58.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 100,000 | 5 | 57.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 9 | 79.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 200,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 9 | 97.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 500,000 | 5 | 94.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 9 | 119.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe331-il | 1,000,000 | 5 | 117.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 50,000 | 9 | 14.3 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 50,000 | 5 | 24.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 100,000 | 9 | 31.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 100,000 | 5 | 44 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 200,000 | 9 | 58 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 500,000 | 9 | 94.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 500,000 | 5 | 91.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 9 | 118.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 5 | 116.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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