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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(fx83w227-il) FX 83-W-227 | Wortmann FX 83-W-227 airfoil for use on wind turbines (W) Max thickness 22.6% at 33.9% chord Max camber 3.4% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(naca65210-il) NACA 65-210 | NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(eh0009-il) EH 0.0/9.0 | John Yost EH 0.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx83w227-il,naca65210-il,eh0009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx83w227-il | 50,000 | 9 | 2.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w227-il | 50,000 | 5 | 7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w227-il | 100,000 | 9 | 8.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w227-il | 100,000 | 5 | 31.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w227-il | 200,000 | 9 | 56.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w227-il | 200,000 | 5 | 50 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w227-il | 500,000 | 9 | 73.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w227-il | 500,000 | 5 | 62.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w227-il | 1,000,000 | 9 | 84.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w227-il | 1,000,000 | 5 | 73.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65210-il | 50,000 | 9 | 24.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65210-il | 50,000 | 5 | 29.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65210-il | 100,000 | 9 | 43.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65210-il | 100,000 | 5 | 43 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65210-il | 200,000 | 9 | 59 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65210-il | 200,000 | 5 | 50.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65210-il | 500,000 | 9 | 72.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65210-il | 500,000 | 5 | 62.7 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca65210-il | 1,000,000 | 9 | 82.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca65210-il | 1,000,000 | 5 | 69.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 50,000 | 9 | 26.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 50,000 | 5 | 26.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 100,000 | 9 | 37.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 100,000 | 5 | 35.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 200,000 | 9 | 47.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 200,000 | 5 | 43.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 500,000 | 9 | 59.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 500,000 | 5 | 55 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 1,000,000 | 9 | 66.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 1,000,000 | 5 | 67.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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