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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(fx74modsm-il) FX 74-Cl5-140 MOD (smoothed) | Modified Wortmann FX 74-CL5-140 high lift airfoil Max thickness 13.1% at 27.1% chord Max camber 9.7% at 41.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx74modsm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74modsm-il | 50,000 | 9 | 6.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 50,000 | 5 | 28.8 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 9 | 41.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 100,000 | 5 | 58.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 9 | 76.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 200,000 | 5 | 84.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 9 | 118.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 500,000 | 5 | 119.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 9 | 152.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74modsm-il | 1,000,000 | 5 | 149.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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