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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(c5e-il) LOCKHEED C-5A BL1256 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 10.8% at 40% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c5e-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c5e-il | 50,000 | 9 | 31.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 50,000 | 5 | 31.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 9 | 46.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 100,000 | 5 | 42.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 9 | 59.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 200,000 | 5 | 47.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 9 | 67.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 500,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 9 | 77.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5e-il | 1,000,000 | 5 | 81 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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