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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(fx78k140-il) FX 78-K-140/20 | Wortmann FX 78-K-140/20 airfoil for use with flaps (K) Max thickness 14.1% at 43.5% chord Max camber 4.4% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx78k140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx78k140-il | 50,000 | 9 | 16.3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 50,000 | 5 | 15 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 100,000 | 9 | 26.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 100,000 | 5 | 27.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 200,000 | 9 | 54.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 200,000 | 5 | 53.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 500,000 | 9 | 125.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 500,000 | 5 | 122.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78k140-il | 1,000,000 | 9 | 162.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78k140-il | 1,000,000 | 5 | 153.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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