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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(fx66196v-il) FX 66-S-196 V1 AIRFOIL | Wortmann FX 66-S-196 V1 airfoil Max thickness 19.6% at 37.1% chord Max camber 4% at 46.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx66196v-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66196v-il | 50,000 | 9 | 4.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 50,000 | 5 | 7.8 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 9 | 5.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 5 | 26.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 9 | 49.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 5 | 61.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 9 | 110.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 5 | 104.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 9 | 139 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 5 | 132.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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