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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(fx63137sm-il) FX 63-137 13.7% smoothed | Wortmann FX 63-137 airfoil (smoothed) Max thickness 13.7% at 30.9% chord Max camber 5.8% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(fx75193-il) WORTMANN FX 75-193 | Wortmann FX 75-193 airfoil Max thickness 19.3% at 40.2% chord Max camber 3.7% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(fxs03182-il) FX S 03-182 AIRFOIL | Wortmann FX S 03-182 airfoil Max thickness 18.2% at 40.2% chord Max camber 2.9% at 56.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx63137sm-il,fx75193-il,fxs03182-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63137sm-il | 50,000 | 9 | 25.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 50,000 | 5 | 31.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 9 | 60.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 100,000 | 5 | 64.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 9 | 91.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 200,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 9 | 125.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 500,000 | 5 | 117.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 9 | 151.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137sm-il | 1,000,000 | 5 | 137.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 9 | 4.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 5 | 11.7 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 9 | 23.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 5 | 22.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 9 | 43.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 5 | 44.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 9 | 91.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 5 | 93.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 9 | 122.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 5 | 120.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs03182-il | 50,000 | 9 | 19.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs03182-il | 50,000 | 5 | 16.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs03182-il | 100,000 | 9 | 27.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs03182-il | 100,000 | 5 | 28.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs03182-il | 200,000 | 9 | 64.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs03182-il | 200,000 | 5 | 66.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs03182-il | 500,000 | 9 | 96.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs03182-il | 500,000 | 5 | 89.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs03182-il | 1,000,000 | 9 | 110.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs03182-il | 1,000,000 | 5 | 96.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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