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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(mh25-il) MH 25 9.98% | Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow) Max thickness 10% at 42.2% chord Max camber 1.4% at 42.2% chord | Remove Airfoil details Airfoil plotter |
(fx61163-il) FX 61-163 AIRFOIL | Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord Max camber 2.6% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(ah80140-il) AH 80-140 | Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh25-il,fx61163-il,ah80140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh25-il | 50,000 | 9 | 34.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 9 | 51.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 5 | 48 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 9 | 70.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 5 | 58.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 5 | 60.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 9 | 75 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 5 | 69.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 9 | 6.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 50,000 | 5 | 19.4 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 9 | 47.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 100,000 | 5 | 50 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 9 | 70.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 200,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 9 | 103.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61163-il | 500,000 | 5 | 98.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 5 | 115.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61163-il | 1,000,000 | 0 | 127.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 50,000 | 9 | 5.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 50,000 | 5 | 14.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 9 | 22.5 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 5 | 35.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 9 | 70.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 5 | 74.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 9 | 116.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 5 | 113.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 9 | 149.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 5 | 139 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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