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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(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 |
(fx77w121-il) FX 77-W-121 | Wortmann FX 77-W-121 airfoil for use on wind turbines (W) Max thickness 12.1% at 30.9% chord Max camber 4.6% at 30.9% chord | Remove Airfoil details Airfoil plotter |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(hq259b-il) HQ 2.5/9 B AIRFOIL | Quabeck HQ 2.5/9 B R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 55% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sg6040-il,fx77w121-il,fx74cl5140-il,hq259b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| fx77w121-il | 50,000 | 9 | 8.1 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w121-il | 50,000 | 5 | 18 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w121-il | 100,000 | 9 | 19 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w121-il | 100,000 | 5 | 37.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w121-il | 200,000 | 9 | 71.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w121-il | 200,000 | 5 | 73.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w121-il | 500,000 | 9 | 115.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w121-il | 500,000 | 5 | 114.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w121-il | 1,000,000 | 9 | 149.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w121-il | 1,000,000 | 5 | 145.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 9 | 39 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 5 | 39.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 9 | 58.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 5 | 56.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 9 | 79.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 5 | 73.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 9 | 105.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 5 | 84.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 9 | 112.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 5 | 91.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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