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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(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL | Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx05h126-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx05h126-il | 50,000 | 9 | 19.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 50,000 | 5 | 14.5 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 9 | 25.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 5 | 24.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 9 | 66.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 5 | 70.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 9 | 121.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 5 | 116.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 9 | 158.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 5 | 145.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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