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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(fx79l100-il) FX 79-L-100 | Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx79l100-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx79l100-il | 50,000 | 9 | 27.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 50,000 | 5 | 27 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 9 | 38.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 5 | 35.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 5 | 41.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 9 | 58 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 9 | 70.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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