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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(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c141e-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c141e-il | 50,000 | 9 | 33.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 9 | 49.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 5 | 45.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 9 | 69.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 5 | 59.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 9 | 88.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 9 | 88.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 5 | 78.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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