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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(fx78pk188-il) FX 78-PK-188/20 | Wortmann FX 78-PK-188/20 variable geometry airfoil Max thickness 18.8% at 43.5% chord Max camber 2.4% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx78pk188-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx78pk188-il | 50,000 | 9 | 18.6 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 50,000 | 5 | 14.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 9 | 24.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 100,000 | 5 | 22.9 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 9 | 38.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 200,000 | 5 | 37.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 9 | 92.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 500,000 | 5 | 91 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 9 | 129.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx78pk188-il | 1,000,000 | 5 | 118.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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