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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(fx63137-il) WORTMANN FX 63-137 AIRFOIL | Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil Max thickness 13.7% at 30.9% chord Max camber 6% at 53.3% chord | Remove Airfoil details Airfoil plotter |
(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 |
(fx78pk188-il) FX 78-PK-188/20 | Wortmann FX 78-PK-188/20 variable geometry airfoil Max thickness 18.8% at 43.5% chord Max camber 2.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL | Gottingen 235 (SCHATTE-LANZ) airfoil Max thickness 6.5% at 19.9% chord Max camber 3.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe275-il) GOE 275 (DAIMLER VI) AIRFOIL | Gottingen 275 (DAIMLER VI) airfoil Max thickness 7.7% at 19.9% chord Max camber 4.7% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx63137-il,fx63137sm-il,fx78pk188-il,goe235-il,goe275-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63137-il | 50,000 | 9 | 26.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 50,000 | 5 | 31.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 9 | 62.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 5 | 63.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 9 | 90.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 5 | 85.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 5 | 103.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 9 | 132.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 5 | 105.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| fx78pk188-il | 50,000 | 9 | 18.6 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 50,000 | 5 | 14.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 9 | 24.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 5 | 22.9 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 9 | 38.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 5 | 37.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 9 | 92.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 5 | 91 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 9 | 129.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 5 | 118.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 9 | 36.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 5 | 37.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 9 | 52.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 5 | 48 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 9 | 60.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 5 | 57.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 9 | 73.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 5 | 68.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 9 | 80.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 5 | 81.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 50,000 | 9 | 34.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 50,000 | 5 | 40.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 100,000 | 9 | 53.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 100,000 | 5 | 55.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 200,000 | 9 | 72 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 200,000 | 5 | 73.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 500,000 | 9 | 99.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 500,000 | 5 | 94.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe275-il | 1,000,000 | 9 | 118.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe275-il | 1,000,000 | 5 | 106.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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