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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(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 |
(clarkv-il) CLARK V AIRFOIL | CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(c141a-il) LOCKHEED C-141 BL0 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 13% at 40.2% chord Max camber 1.1% at 64.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarkw-il,clarkv-il,c141a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| clarkv-il | 50,000 | 9 | 35.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 50,000 | 5 | 36.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 100,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 9 | 80.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 200,000 | 5 | 75.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 9 | 110.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 500,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 9 | 129.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkv-il | 1,000,000 | 5 | 105.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 50,000 | 9 | 29 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 50,000 | 5 | 27.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 9 | 44.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 100,000 | 5 | 42 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 9 | 62 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 200,000 | 5 | 47.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 9 | 67.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 500,000 | 5 | 59.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 9 | 76.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141a-il | 1,000,000 | 5 | 72.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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