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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(fx75193-il) WORTMANN FX 75-193 | Wortmann FX 75-193 airfoil Max thickness 19.3% at 40.2% chord Max camber 3.7% at 69.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx75193-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx75193-il | 50,000 | 9 | 4.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 5 | 11.7 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 9 | 23.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 5 | 22.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 9 | 43.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 5 | 44.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 9 | 91.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 5 | 93.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 9 | 122.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 5 | 120.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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