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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(fx63158-il) FX 63-158 AIRFOIL | Wortmann FX 63-158 airfoil Max thickness 15.8% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx63158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63158-il | 50,000 | 9 | 6.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 50,000 | 5 | 18.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 100,000 | 5 | 51.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 9 | 72.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 200,000 | 5 | 67.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 9 | 76.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 500,000 | 5 | 70.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 9 | 85 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63158-il | 1,000,000 | 5 | 81.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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