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 |
(la203a-il) DOUGLAS LA203A AIRFOIL | Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sg6042-il,la203a-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 | |
| la203a-il | 50,000 | 9 | 6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 5 | 13.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 9 | 30.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 5 | 46.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 9 | 82.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 5 | 85.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 9 | 127.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 9 | 160.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 5 | 151.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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