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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(fxs02196-il) FX S 02-196 AIRFOIL | Wortmann FX S 02-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.7% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fxs02196-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fxs02196-il | 50,000 | 9 | 4.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 50,000 | 5 | 10.2 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 9 | 16.8 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 100,000 | 5 | 37.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 9 | 68.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 9 | 53.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 500,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 9 | 60.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs02196-il | 1,000,000 | 5 | 54.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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