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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(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 |
(ag44ct02r-il) AG44ct -02f | Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c141a-il,ag44ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| ag44ct02r-il | 50,000 | 9 | 30.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 50,000 | 5 | 34.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 9 | 45.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 5 | 47.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 9 | 61.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 5 | 60.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 9 | 82.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 5 | 78.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 9 | 97.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 5 | 91.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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