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 |
(clarkysm-il) CLARK-Y 11.7% smoothed | CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord Max camber 3.5% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
(clarkw-il) CLARK W AIRFOIL | CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarky-il,clarkysm-il,cast102-il,clarkw-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 | |
| clarkysm-il | 50,000 | 9 | 30 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 50,000 | 5 | 35.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 9 | 52.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 5 | 53.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 9 | 74.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 9 | 101.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 5 | 90.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 9 | 119.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 5 | 106.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 9 | 32.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 50,000 | 5 | 36.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 9 | 53.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 100,000 | 5 | 54.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 9 | 73.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 200,000 | 5 | 69.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 9 | 98.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 500,000 | 5 | 91.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 9 | 116.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkw-il | 1,000,000 | 5 | 107.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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