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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(clarkz-il) CLARK Z AIRFOIL | CLARK Z airfoil Max thickness 11.8% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarkz-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkz-il | 50,000 | 9 | 30.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkz-il | 50,000 | 5 | 36.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkz-il | 100,000 | 9 | 54 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkz-il | 100,000 | 5 | 55.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkz-il | 200,000 | 9 | 74.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkz-il | 200,000 | 5 | 72.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkz-il | 500,000 | 9 | 100.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkz-il | 500,000 | 5 | 93.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkz-il | 1,000,000 | 9 | 120.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkz-il | 1,000,000 | 5 | 109.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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