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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(clarkk-il) CLARK K AIRFOIL | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarkk-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkk-il | 50,000 | 9 | 32.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 9 | 54.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 5 | 54.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 9 | 75.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 5 | 71.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 9 | 102.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 5 | 91.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 9 | 121.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 5 | 104.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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