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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(fx66h80-il) FX 66-H-80 | Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(fx66h60-il) FX 66-H-60 | Wortmann FX 66-H-60 airfoil Max thickness 6% at 22.2% chord Max camber 1.7% at 17% chord | Remove Airfoil details Airfoil plotter |
(fx71089a-il) WORTMANN FX 71-089A AIRFOIL | Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx66h80-il,fx66h60-il,fx71089a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66h80-il | 50,000 | 9 | 32.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 5 | 31.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 9 | 47.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 5 | 47.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 9 | 63 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 5 | 62.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 9 | 87.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 5 | 83.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 9 | 105.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 5 | 98.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 9 | 28.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 50,000 | 5 | 29.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 9 | 37.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 100,000 | 5 | 40.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 9 | 51.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 200,000 | 5 | 51.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 9 | 69.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 500,000 | 5 | 67.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 9 | 84.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h60-il | 1,000,000 | 5 | 76.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 9 | 19.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 5 | 19.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 5 | 26.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 9 | 31.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 5 | 36.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 5 | 52.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 9 | 59.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 5 | 68 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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