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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(fxs21158-il) FX S 02/1-158 AIRFOIL | Wortmann FX S 02/1-158 airfoil Max thickness 15.8% at 30.9% chord Max camber 3.5% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fxs21158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fxs21158-il | 50,000 | 9 | 5.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs21158-il | 50,000 | 5 | 18.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs21158-il | 100,000 | 9 | 37.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs21158-il | 100,000 | 5 | 47.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs21158-il | 200,000 | 9 | 76.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs21158-il | 200,000 | 5 | 72.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs21158-il | 500,000 | 9 | 96.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs21158-il | 500,000 | 5 | 87.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxs21158-il | 1,000,000 | 9 | 105.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxs21158-il | 1,000,000 | 5 | 76 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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