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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(naca001064-il) NACA 0010-64 | NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx62k131-il) WORTMANN FX 62-K-131 AIRFOIL | Wortmann FX 62-K-131/17 airfoil Max thickness 13.1% at 40.2% chord Max camber 3.9% at 53.3% chord | Remove Airfoil details Airfoil plotter |
(fx84w097-il) FX 84-W-097 | Wortmann FX 84-W-097 airfoil for use on wind turbines (W) Max thickness 9.7% at 33.9% chord Max camber 2.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca001064-il,fx62k131-il,fx84w097-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca001064-il | 50,000 | 9 | 25.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 50,000 | 5 | 25.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 100,000 | 9 | 36.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 100,000 | 5 | 31.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 200,000 | 9 | 43.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 200,000 | 5 | 38.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 500,000 | 9 | 49.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 500,000 | 5 | 53.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001064-il | 1,000,000 | 9 | 62.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001064-il | 1,000,000 | 5 | 71.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 50,000 | 5 | 29 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 50,000 | 0 | 30.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k131-il | 100,000 | 5 | 55.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 100,000 | 0 | 56.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k131-il | 200,000 | 5 | 84.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 200,000 | 0 | 83.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k131-il | 500,000 | 5 | 125.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 500,000 | 0 | 124 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx62k131-il | 1,000,000 | 5 | 153.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx62k131-il | 1,000,000 | 0 | 162.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 50,000 | 9 | 36.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 50,000 | 5 | 36.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w097-il | 100,000 | 9 | 56.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 100,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w097-il | 200,000 | 9 | 76.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 200,000 | 5 | 73.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w097-il | 500,000 | 9 | 104.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 500,000 | 5 | 96.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w097-il | 1,000,000 | 9 | 123.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w097-il | 1,000,000 | 5 | 112.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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