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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(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord | Remove Airfoil details Airfoil plotter |
(e222-il) E222 (10.17%) | Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord | Remove Airfoil details Airfoil plotter |
(e473-il) EPPLER 473 AIRFOIL | Eppler E473 aerobatic aircraft airfoil Max thickness 16.2% at 21.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (c141f-il,c5c-il,e222-il,e473-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| c141f-il | 50,000 | 9 | 34.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 9 | 50.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 100,000 | 5 | 46.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 9 | 69.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 200,000 | 5 | 59.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 9 | 89 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 500,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 9 | 89.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141f-il | 1,000,000 | 5 | 86.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 9 | 31.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 5 | 30.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 9 | 48.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 5 | 44.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 9 | 67.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 5 | 55.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 9 | 78.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 5 | 62.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 9 | 82.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 5 | 77.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 50,000 | 9 | 36.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 50,000 | 5 | 38.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 100,000 | 9 | 56.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 100,000 | 5 | 55.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 200,000 | 9 | 76.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 200,000 | 5 | 71.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 500,000 | 9 | 101.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 500,000 | 5 | 89.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 9 | 118.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 5 | 99.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 50,000 | 9 | 15.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 50,000 | 5 | 21.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 100,000 | 9 | 26.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 100,000 | 5 | 35.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 200,000 | 9 | 47.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 200,000 | 5 | 53.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 500,000 | 9 | 78.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 500,000 | 5 | 78.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e473-il | 1,000,000 | 9 | 101.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e473-il | 1,000,000 | 5 | 95.7 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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