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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(clarky-il) CLARK Y AIRFOIL | CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarky-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarky-il | 50,000 | 9 | 29.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 9 | 73.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 200,000 | 5 | 69.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 9 | 98.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 500,000 | 5 | 90.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 9 | 114.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarky-il | 1,000,000 | 5 | 108.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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