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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(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 |
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Polars for (fx74cl5140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
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