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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(clarym15-il) CLARK YM-15 AIRFOIL | CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarym15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarym15-il | 50,000 | 9 | 12.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 5 | 31 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 9 | 47.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 5 | 48.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 9 | 66.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 5 | 62.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 5 | 84.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 9 | 109.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 5 | 105.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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