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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(m25-il) NACA M25 AIRFOIL | NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(fx79w660a-il) FX 79-W-660A | Wortman FX 79-W-660A airfoil for use on wind turbines (W) Max thickness 66.4% at 46.7% chord Max camber 2.3% at 17% chord | Remove Airfoil details Airfoil plotter |
(goe428-il) GOE 428 AIRFOIL | Gottingen 428 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL | Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m25-il,fx79w660a-il,goe428-il,vr11x-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m25-il | 50,000 | 9 | 6.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 50,000 | 5 | 20.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 100,000 | 9 | 53.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 100,000 | 5 | 54.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 200,000 | 9 | 78.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 200,000 | 5 | 78.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 500,000 | 9 | 102.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 500,000 | 5 | 94.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 9 | 111.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m25-il | 1,000,000 | 5 | 107.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 9 | 0.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 50,000 | 5 | 3 at α=-10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 9 | 5.2 at α=-10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 100,000 | 5 | 5.5 at α=-5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 9 | 8.7 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 200,000 | 5 | 6 at α=-2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 9 | 5 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 500,000 | 5 | 4.7 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 9 | 6.5 at α=16.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79w660a-il | 1,000,000 | 5 | 5.4 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe428-il | 50,000 | 9 | 38.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe428-il | 50,000 | 5 | 40.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe428-il | 100,000 | 9 | 58.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe428-il | 100,000 | 5 | 60.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe428-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe428-il | 200,000 | 5 | 78.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe428-il | 500,000 | 9 | 104.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe428-il | 500,000 | 5 | 102.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe428-il | 1,000,000 | 9 | 125 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe428-il | 1,000,000 | 5 | 121.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 9 | 30.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 5 | 29.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 9 | 41 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 5 | 39.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 9 | 55.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 5 | 51.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 9 | 71.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 9 | 92.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 5 | 89.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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