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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(fx83w160-il) FX 83-W-160 | Wortmann FX 83-W-160 airfoil for use on wind turbines (W) Max thickness 16.1% at 37.1% chord Max camber 3.9% at 62.9% chord | Remove Airfoil details Airfoil plotter |
(raf89-il) RAF 89 AIRFOIL | RAF-89 airfoil Max thickness 25% at 30% chord Max camber 1.6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx83w160-il,raf89-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx83w160-il | 50,000 | 9 | 30 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w160-il | 50,000 | 5 | 24.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w160-il | 100,000 | 9 | 45.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w160-il | 100,000 | 5 | 42.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w160-il | 200,000 | 9 | 76.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w160-il | 200,000 | 5 | 69.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w160-il | 500,000 | 9 | 109.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w160-il | 500,000 | 5 | 96.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx83w160-il | 1,000,000 | 9 | 131.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx83w160-il | 1,000,000 | 5 | 109.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 9 | 1.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 5 | 7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 9 | 18.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 5 | 27.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 9 | 45.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 5 | 36 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 9 | 50.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 5 | 39.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 9 | 56.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 5 | 45.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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