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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(fx73170a-il) WORTMANN FX 73-170 A | Wortmann FX 73-170 A airfoil Max thickness 17.1% at 43.5% chord Max camber 5.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73170a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73170a-il | 50,000 | 9 | 4.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 50,000 | 5 | 11.1 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 100,000 | 9 | 18.1 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 100,000 | 5 | 17.4 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 200,000 | 9 | 31.2 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 200,000 | 5 | 51.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 500,000 | 9 | 117.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 500,000 | 5 | 110.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73170a-il | 1,000,000 | 9 | 151.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73170a-il | 1,000,000 | 5 | 144 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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