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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(fx38153-il) FX 38-153 AIRFOIL | Wortmann FX 38-153 airfoil Max thickness 15.5% at 43.5% chord Max camber 2.1% at 80.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx38153-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx38153-il | 50,000 | 9 | 31.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 50,000 | 5 | 26.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 9 | 46.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 100,000 | 5 | 36.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 9 | 46.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 200,000 | 5 | 47.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 500,000 | 5 | 60.8 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 9 | 91.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx38153-il | 1,000,000 | 5 | 64.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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