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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(sg6042-il) SG6042 | Selig / Giguere SG6042 wind turbine airfoil (high L/D) Max thickness 10% at 33.5% chord Max camber 3.3% at 51.5% chord | Remove Airfoil details Airfoil plotter |
(sg6041-il) SG6041 | Selig / Giguere SG6041 wind turbine airfoil (high L/D) Max thickness 10% at 34.9% chord Max camber 1.6% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(sm701-il) SM701 | Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord Max camber 3% at 60.3% chord | Remove Airfoil details Airfoil plotter |
(sg6040-il) SG6040 | Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sg6042-il,sg6041-il,sm701-il,sg6040-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sg6042-il | 50,000 | 9 | 40 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 50,000 | 5 | 39.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 9 | 62.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 5 | 60.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 9 | 89 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 5 | 82.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 9 | 123.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 5 | 106.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 9 | 145.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 5 | 110.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 50,000 | 9 | 35.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 50,000 | 5 | 35.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 100,000 | 9 | 53.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 100,000 | 5 | 49.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 200,000 | 9 | 72.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 200,000 | 5 | 63.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 500,000 | 9 | 91.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 500,000 | 5 | 74.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6041-il | 1,000,000 | 9 | 96.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6041-il | 1,000,000 | 5 | 88 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 9 | 27 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 5 | 30.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 9 | 50.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 5 | 46.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 9 | 68.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 5 | 64.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 9 | 95.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 5 | 79.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 9 | 110.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 5 | 93.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 50,000 | 9 | 26.1 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 50,000 | 5 | 26.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 9 | 50.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 9 | 72.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 200,000 | 5 | 68.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 9 | 96.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 500,000 | 5 | 88.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 9 | 114.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6040-il | 1,000,000 | 5 | 102.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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