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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(fx049915-il) WORTMANN FX 049-915 AIRFOIL | Wortmann FX 049-915 airfoil Max thickness 14.7% at 37.1% chord Max camber 5.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx049915-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx049915-il | 50,000 | 9 | 4.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 50,000 | 5 | 10.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 100,000 | 9 | 6.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 100,000 | 5 | 24.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 200,000 | 9 | 25.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 200,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 500,000 | 9 | 113.5 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 500,000 | 5 | 114.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx049915-il | 1,000,000 | 9 | 155 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx049915-il | 1,000,000 | 5 | 152.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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